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Sample records for hard mobile launcher

  1. Small ICBM area narrowing report. Volume 1. Hard mobile launcher in random movement basing mode

    SciTech Connect

    Not Available

    1986-01-01

    The purpose of this report is to identify those areas that could potentially support deployment of the Small Intercontinental Ballistic Missile (ICBM) utilizing basing modes presently considered viable: the Hard Mobile Launcher in Random Movement, the Hard Mobile Launcher at Minuteman Facilities, and the Hard Silo in Patterned Array. Specifically, this report describes the process and the rationale supporting the application of Exclusionary and Evaluative Criteria and lists those locations that were eliminated through the application of these criteria. The remaining locations will be the subject of further investigations.

  2. Small ICBM area narrowing report. Volume 2. Hard mobile launcher at minuteman facilities basing mode

    SciTech Connect

    Not Available

    1986-01-01

    The purpose of this report is to identify those areas that could potentially support deployment of the Small Intercontinental Ballistic Missile (ICBM) utilizing basing modes presently considered viable: the Hard Mobile Launcher in Random Movement, the Hard Mobile Launcher at Minuteman Facilities, and the Hard Silo in Patterned Array. Specifically, this report describes the process and the rationale supporting the application of Exclusionary and Evaluative Criteria and lists those locations that were eliminated through the application of these criteria. The remaining locations will be the subject of further investigations.

  3. Mobile Launcher Moves for Testing

    NASA Image and Video Library

    In anticipation of launching NASA’s Space Launch System heavy-lift rocket later in this decade, engineers wanted to check the mobile launcher, or ML, to see how it would behave moving atop a craw...

  4. Time lapse: Mobile Launcher Moves

    NASA Image and Video Library

    The mobile launcher returned from Launch Pad 39B at NASA's Kennedy Space Center in Florida following two weeks of structural and other testing. The 355-foot-tall structure is to be used by the Spac...

  5. Long Exposure Photos of Mobile Launcher

    NASA Image and Video Library

    2017-03-14

    A long-exposure view of the mobile launcher at NASA's Kennedy Space Center in Florida. Cranes and rigging are being used to lift the bracket for the Orion Service Module Umbilical (OSMU) up for installation on the mobile launcher tower. The tower will be equipped with a number of lines, called umbilicals, that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The OSMU will be located high on the mobile launcher tower and, prior to launch, will transfer liquid coolant for the electronics and air for the Environmental Control System to the Orion service module that houses these critical systems to support the spacecraft. EM-1 is scheduled to launch in 2018. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  6. 6. MOBILE LAUNCHER SIDE 4, SHOWING MILK STOOL AND LUT. ...

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

    6. MOBILE LAUNCHER SIDE 4, SHOWING MILK STOOL AND LUT. PROTRUSION ON UPPER RIGHT HAND SIDE OF LUT IS SWING ARM NINE WHICH PROVIDED ACCESS TO CAPSULE OF LAUNCH VEHICLE WHILE ON LAUNCHER. - Mobile Launcher One, Kennedy Space Center, Titusville, Brevard County, FL

  7. Vehicle Support Posts Installation at Mobile Launcher

    NASA Image and Video Library

    2017-05-11

    Construction workers at the Mobile Launcher at NASA's Kennedy Space Center in Florida, prepare to install vehicle support posts. A total of eight support posts are being installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  8. 3. AERIAL VIEW OF MOBILE LAUNCHER. ON TOP OF LUT ...

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

    3. AERIAL VIEW OF MOBILE LAUNCHER. ON TOP OF LUT SITS A 25 TON HAMMERHEAD CRANE. STRUCTURE ON LEFT SIDE OF LAUNCH PLATFORM IS KNOWN AS A 'MILK STOOL' AND ALLOWS A SATURN 1B ROCKET TO BE USED IN PLACE OF THE SATURN V ROCKET. - Mobile Launcher One, Kennedy Space Center, Titusville, Brevard County, FL

  9. Core Stage Forward Skirt Umbilical Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-06-29

    Just north of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, the core stage forward skirt umbilical is installed on the mobile launcher. The mobile launcher is designed to support the assembly, testing and check-out of the agency's Space Launch System (SLS) rocket and the Orion spacecraft.

  10. Vehicle Support Posts Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-05-25

    At NASA's Kennedy Space Center in Florida, the final four vehicle support posts are being installed on the deck of the mobile launcher. A total of eight support posts are being installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  11. Vehicle Support Posts Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-05-25

    Construction workers on the deck of the mobile launcher at NASA's Kennedy Space Center in Florida, prepare to install a vehicle support post. A total of eight support posts are being installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  12. Vehicle Support Posts Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-05-11

    In view are three vehicle support posts installed on the deck of the mobile launcher at NASA's Kennedy Space Center in Florida. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  13. Vehicle Support Posts Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-05-11

    A vehicle support post will lifted up by crane and lowered onto the deck of the mobile launcher at NASA's Kennedy Space Center in Florida. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  14. Vehicle Support Posts Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-05-11

    A construction worker on the deck of the mobile launcher welds a portion of a platform for installation of a vehicle support post at NASA's Kennedy Space Center in Florida. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  15. Vehicle Support Posts Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-05-11

    Construction workers on the deck of the mobile launcher at NASA's Kennedy Space Center in Florida, prepare a platform for installation of a vehicle support post. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  16. Vehicle Support Posts Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-05-11

    Four vehicle support posts have been installed on the deck of the mobile launcher at NASA's Kennedy Space Center in Florida. A total of eight support posts will be installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  17. Vehicle Support Posts Installation onto Mobile Launcher

    NASA Image and Video Library

    2017-05-25

    At NASA's Kennedy Space Center in Florida, construction workers on the deck of the mobile launcher install the final four vehicle support posts. A total of eight support posts are being installed to support the load of the Space Launch System's (SLS) solid rocket boosters, with four posts for each of the boosters. The support posts are about five feet tall and each weigh about 10,000 pounds. The posts will structurally support the SLS rocket through T-0 and liftoff, and will drop down before vehicle liftoff to avoid contact with the flight hardware. The Ground Systems Development and Operations Program is overseeing installation of the support posts to prepare for the launch of the Orion spacecraft atop the SLS rocket.

  18. Time-Lapse: Mobile Launcher Moves to Launch Pad

    NASA Image and Video Library

    The mobile launcher that will host NASA's Space Launch System and new Orion spacecraft was moved to Launch Pad 39B at NASA's Kennedy Space Center in Florida to begin two weeks of structural and sys...

  19. Dr. Wernher Von Braun near the mobile launcher.

    NASA Technical Reports Server (NTRS)

    1999-01-01

    Dr. George Mueller, NASA associate administrator for manned space flight, and Dr. Wernher Von Braun (right), director of the Marshall Space Flight Center, are seen near the mobile launcher carrying a 363 foot tall Saturn V space launch vehicle as the rocket is rolled from the vehicle assembly building at KSC for its three mile trip to the launch pad.

  20. Dr. Wernher Von Braun near the mobile launcher.

    NASA Technical Reports Server (NTRS)

    1999-01-01

    Dr. George Mueller, NASA associate administrator for manned space flight, and Dr. Wernher Von Braun (right), director of the Marshall Space Flight Center, are seen near the mobile launcher carrying a 363 foot tall Saturn V space launch vehicle as the rocket is rolled from the vehicle assembly building at KSC for its three mile trip to the launch pad.

  1. Orion Service Module Umbilical (OSMU) Installation on Mobile Launcher (ML)

    NASA Image and Video Library

    2017-03-13

    Cranes and rigging are being used to lift the bracket for the Orion Service Module Umbilical (OSMU) up for installation on the mobile launcher tower. The tower will be equipped with a number of lines, called umbilicals, that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The OSMU will be located high on the mobile launcher tower and, prior to launch, will transfer liquid coolant for the electronics and air for the Environmental Control System to the Orion service module that houses these critical systems to support the spacecraft. EM-1 is scheduled to launch in 2018. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  2. Acoustic and Vibration Environment for Crew Launch Vehicle Mobile Launcher

    NASA Technical Reports Server (NTRS)

    Vu, Bruce T.

    2007-01-01

    A launch-induced acoustic environment represents a dynamic load on the exposed facilities and ground support equipment (GSE) in the form of random pressures fluctuating around the ambient atmospheric pressure. In response to these fluctuating pressures, structural vibrations are generated and transmitted throughout the structure and to the equipment items supported by the structure. Certain equipment items are also excited by the direct acoustic input as well as by the vibration transmitted through the supporting structure. This paper presents the predicted acoustic and vibration environments induced by the launch of the Crew Launch Vehicle (CLV) from Launch Complex (LC) 39. The predicted acoustic environment depicted in this paper was calculated by scaling the statistically processed measured data available from Saturn V launches to the anticipated environment of the CLV launch. The scaling was accomplished by using the 5-segment Solid Rocket Booster (SRB) engine parameters. Derivation of vibration environment for various Mobile Launcher (ML) structures throughout the base and tower was accomplished by scaling the Saturn V vibration environment.

  3. VIEW OF HB1 (VAB HIGH BAY) WITH MOBILE LAUNCHER PLATFORM ...

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

    VIEW OF HB-1 (VAB HIGH BAY) WITH MOBILE LAUNCHER PLATFORM (VEHICLE ACCESS PLATFORMS ARE VISIBLE IN THE CENTER), FACING WEST - Cape Canaveral Air Force Station, Launch Complex 39, Vehicle Assembly Building, VAB Road, East of Kennedy Parkway North, Cape Canaveral, Brevard County, FL

  4. STS-30 Atlantis, OV-104, at KSC LC Pad 39B atop mobile launcher platform

    NASA Technical Reports Server (NTRS)

    1989-01-01

    STS-30 Atlantis, Orbiter Vehicle (OV) 104, arrives at Kennedy Space Center (KSC) Launch Complex (LC) Pad 39B atop mobile launcher platform. The fixed service structure (FSS) towers above OV-104, its external tank (ET), and its solid rocket boosters (SRBs). The rotating service structure (RSS) is retracted. The launch tower catwalks are also retracted.

  5. Workers in the VAB move sling into place to lift Columbia to mobile launcher

    NASA Technical Reports Server (NTRS)

    1982-01-01

    Workers in the Vehicle Assembly Building (VAB) move a specially-built sling into place to lift Orbiter Columbia from the transfer aisle to the mobile launcher platform (27015); Columbia is lifted from the floor of the VAB transfer aisle (27016).

  6. STS-30 Atlantis, OV-104, on the mobile launcher platform heads to KSC LC pad

    NASA Technical Reports Server (NTRS)

    1989-01-01

    STS-30 Atlantis, Orbiter Vehicle (OV) 104, riding atop the mobile launcher platform and the crawler transporter approaches Kennedy Space Center (KSC) Launch Complex (LC) pad 39B. This backlit view highlights OV-104's profile, the external tank (ET), and one of the two solid rocket boosters (SRBs) as it moves up LC pad 39B incline.

  7. Utilizing NX Advanced Simulation for NASA's New Mobile Launcher for Ares-l

    NASA Technical Reports Server (NTRS)

    Brown, Christopher

    2010-01-01

    This slide presentation reviews the use of NX to simulate the new Mobile Launcher (ML) for the Ares-I. It includes: a comparison of the sizes of the Saturn 5, the Space Shuttle, the Ares I, and the Ares V, with the height, and payload capability; the loads control plan; drawings of the base framing, the underside of the ML, beam arrangement, and the finished base and the origin of the 3D CAD data. It also reviews the modeling approach, meshing. the assembly Finite Element Modeling, the model summary. and beam improvements.

  8. The STS-93 external tank and booster stack sits at the Mobile Launcher Platform park site

    NASA Technical Reports Server (NTRS)

    1999-01-01

    The STS-93 stack of solid rocket boosters and external tank sits at the Mobile Launcher Platform park site waiting for lightning shield wires to be installed on the Vehicle Assembly Building (VAB) in the background. The stack is being temporarily stored outside the VAB while Space Shuttle Discovery undergoes repair to hail damage in High Bay 1. Discovery was rolled back from Pad 39B to the VAB for repairs because access to all of the damaged areas was not possible at the pad. The STS-93 stack will be moved under the wires at the VAB for protection until Discovery returns to the pad, later this week. The scheduled date for launch of mission STS-96 is no earlier than May 27. STS-93 is targeted for launch on July 22, carrying the Chandra X-ray Observatory.

  9. KENNEDY SPACE CENTER, FLA. - Sandblasting begins on the Mobile Launcher Platform on Launch Pad 39A to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

    NASA Image and Video Library

    2003-09-12

    KENNEDY SPACE CENTER, FLA. - Sandblasting begins on the Mobile Launcher Platform on Launch Pad 39A to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

  10. KENNEDY SPACE CENTER, FLA. - A worker sandblasts the surface behind the Mobile Launcher Platform on Launch Pad 39A . Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

    NASA Image and Video Library

    2003-09-12

    KENNEDY SPACE CENTER, FLA. - A worker sandblasts the surface behind the Mobile Launcher Platform on Launch Pad 39A . Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

  11. KENNEDY SPACE CENTER, FLA. - On Launch Pad 39A, clouds of dust float away from the Mobile Launcher Platform, which is undergoing sandblasting to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

    NASA Image and Video Library

    2003-09-12

    KENNEDY SPACE CENTER, FLA. - On Launch Pad 39A, clouds of dust float away from the Mobile Launcher Platform, which is undergoing sandblasting to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

  12. Chartering Launchers for Small Satellites

    NASA Astrophysics Data System (ADS)

    Hernandez, Daniel

    The question of how to launch small satellites has been solved over the years by the larger launchers offering small satellites the possibility of piggy-backing. Specific fixtures have been developed and commercialized: Arianespace developed the ASAP interface, the USAF studied ESPA, NASA has promoted Shuttle launch possibilities, Russian authorities and companies have been able to find solutions with many different launchers... It is fair to say that most launcher suppliers have worked hard and finally often been able to find solutions to launch most small satellites into orbit. It is also true, however, that most of these small satellites were technology demonstration missions capable of accepting a wide range of orbit and launch characteristics: orbit altitude and inclination, launch date, etc. In some cases the small satellite missions required a well-defined type of orbit and have therefore been obliged to hire a small launcher on which they were the prime passenger. In our paper we would like to propose an additional solution to all these possibilities: launchers could plan well in advance (for example about 3 years), trips to precisely defined orbits to allow potential passengers to organize themselves and be ready on the D-Day. On the scheduled date the chartered launcher goes to the stated orbit while on another date, another chartered launcher goes to another orbit. The idea is to organize departures for space like trains or airplanes leaving on known schedules for known destinations.

  13. Small ICBM Area Narrowing Report. Volume 1. Hard Mobile Launcher in Random Movement Basing Mode

    DTIC Science & Technology

    1986-01-01

    AF 4 NM MELROSE AIR FORCE RANGE AF 3 NM SACRAMENTO PEAK JARS AF 3 NM WHITE SANDS MISSILE RANGE ARMY NV FALLON NAVAL AIR STATION NAVY 4 NV HAWTHORNE ...STATION NAVY 4 RI NEWPORT EDUCATION & TRAINING CENTER NAVY 3 RI DAVISVILLE CONST. BATTALION CTR NAVY 4 RI FORT NATHANIEL GREEN ARMY 4 RI PROVIDENCE NAVAL

  14. Small ICBM Area Narrowing Report. Volume 2. Hard Mobile Launcher at Minuteman Facilities Basing Mode

    DTIC Science & Technology

    1986-01-01

    region indicates the potential for inmigration of project-related workers. 3 Low regional employment in the construction and military sectors...of goods and services is limited. 3 Nonagricultural employment in the region indicates the potential for inmigration of project-related workers. 3 Low ...employment in the region indicates the potential for 3 inmigration of project-related workers. Low regional employment in the construction and

  15. Grenade Launchers

    DTIC Science & Technology

    1987-03-13

    energy (if specified in the test plan) (c) Force and stroke required Lo manually operate the trigger (e) Charging force (f) Test launcher length, width...Conduct nondestructive test ( NDT ) inspections of weapon components sub- jected to high stress during firing (bolt, sear, barrel, gas piston, etc...applicable, conduct NDT inspections of weapon components subject to high stress during firing. At the same intervals, record the follow- ing suggested

  16. Rotating mobile launcher

    NASA Technical Reports Server (NTRS)

    Gregory, T. J.

    1977-01-01

    Apparatus holds remotely piloted arm that accelerates until launching speed is reached. Then vehicle and counterweight at other end of arm are released simultaneously to avoid structural damage from unbalanced rotating forces.

  17. Electromagnetic launchers

    NASA Astrophysics Data System (ADS)

    Kolm, H.; Mongeau, P.; Williams, F.

    1980-09-01

    Recent advances in energy storage, switching and magnet technology make electromagnetic acceleration a viable alternative to chemical propulsion for certain tasks, and a means to perform other tasks not previously feasible. Applications include the acceleration of gram-size particles for hypervelocity research and the initiation of fusion by impact, a replacement for chemically propelled artillery, the transportation of cargo and personnel over inaccessible terrain, and the launching of space vehicles to supply massive space operations, and for the disposal of nuclear waste. The simplest launcher of interest is the railgun, in which a short-circuit slide or an arc is driven along two rails by direct current. The most sophisticated studied thus far is the mass driver, in which a superconducting shuttle bucket is accelerated by a line of pulse coils energized by capacitors at energy conversion efficiencies better than 90%. Other accelerators of interest include helical, brush-commutated motors, discrete coil arc commutated drivers, flux compression momentum transformers, and various hybrid electrochemical devices.

  18. Electromagnetic launcher

    SciTech Connect

    Laskaris, E.T.; Chari, M.V.K.

    1990-11-20

    This paper describes an electromagnetic launcher. It comprises: a stationary superconductive coil situated coaxially in a cylindrical vacuum vessel for providing a magnetic field. The superconductive coil having a central aperture, the vacuum vessel having an axially extending bore passing through the central aperture of the superconducting coil; a resistive coil situated coaxially with the superconductive coil and movable axially relative to the stationary superconductive coil, the outer diameter of the resistive coil being smaller than the inner diameter of the bore permitting the resistive coil to pass therethrough; launch activating means coupled to the resistive coil. The launch activating means comprising a shaft joined at one end to the resistive coil, a tube open at both ends, a sliding piston situated in the tube and connected to the other end of the shaft; and power supply means coupled to the resistive coil for providing current of a desired direction and magnitude, so that energization of the resistive coil in the presence of the radial field component of the magnetic field of the superconductive coil creates an axial force on the movable coil, the direction and magnitude of which is dependent on the direction and magnitude of the current in the resistive coil.

  19. 5. VAL LAUNCHER BRIDGE OVER LAUNCHER SLAB TAKEN FROM RESERVOIR ...

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

    5. VAL LAUNCHER BRIDGE OVER LAUNCHER SLAB TAKEN FROM RESERVOIR LOOKING NORTH. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  20. 27. VAL, DETAIL OF LAUNCHER SLAB AND LAUNCHER RAIL WITH ...

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

    27. VAL, DETAIL OF LAUNCHER SLAB AND LAUNCHER RAIL WITH 7 INCH DIAMETER HOLE FOR SUPPORT CARRIAGE LOCKING PIN. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  1. Lightweight Composite Launcher Pod.

    DTIC Science & Technology

    This patent application discloses a lightweight composite launcher pod which includes a multiplicity of elongated launcher tubes that are accurately...alignment surfaces on the other side, and the lightweight composite launcher pod being capable of serving as the shipping and storage container for

  2. Generic Software Architecture for Launchers

    NASA Astrophysics Data System (ADS)

    Carre, Emilien; Gast, Philippe; Hiron, Emmanuel; Leblanc, Alain; Lesens, David; Mescam, Emmanuelle; Moro, Pierre

    2015-09-01

    The definition and reuse of generic software architecture for launchers is not so usual for several reasons: the number of European launcher families is very small (Ariane 5 and Vega for these last decades); the real time constraints (reactivity and determinism needs) are very hard; low levels of versatility are required (implying often an ad hoc development of the launcher mission). In comparison, satellites are often built on a generic platform made up of reusable hardware building blocks (processors, star-trackers, gyroscopes, etc.) and reusable software building blocks (middleware, TM/TC, On Board Control Procedure, etc.). If some of these reasons are still valid (e.g. the limited number of development), the increase of the available CPU power makes today an approach based on a generic time triggered middleware (ensuring the full determinism of the system) and a centralised mission and vehicle management (offering more flexibility in the design and facilitating the long term maintenance) achievable. This paper presents an example of generic software architecture which could be envisaged for future launchers, based on the previously described principles and supported by model driven engineering and automatic code generation.

  3. Small ICBM area narrowing report. Volume 3: Hard silo in patterned array basing mode

    SciTech Connect

    Not Available

    1986-01-01

    The purpose of this report is to identify those areas that could potentially support deployment of the Small Intercontinental Ballistic Missile (ICBM) utilizing basing modes presently considered viable: the Hard Mobile Launcher in Random Movement, the Hard Mobile Launcher at Minuteman Facilities, or the Hard Silo in Patterned Array. Specifically, this report describes the process and the rationale supporting the application of Exclusionary and Evaluative Criteria and lists those locations that were eliminated through the application of these criteria. The remaining locations will be the subject of further investigations.

  4. Lightweight composite launcher pod

    NASA Astrophysics Data System (ADS)

    Hoffmeister, L. D.; Thompson, R. J.

    1984-08-01

    This patent application discloses a lightweight composite launcher pod which includes a multiplicity of elongated launcher tubes that are accurately aligned in a composite material with the composite material having four outer sides with alignment surfaces on three of the sides and bearing and alignment surfaces on the other side, and the lightweight composite launcher pod being capable of serving as the shipping and storage container for rockets before launching of the rockets as well as for launching the rockets therefrom when mounted in a launcher structure.

  5. 4. VAL PARTIAL ELEVATION SHOWING LAUNCHER BRIDGE ON SUPPORTS, LAUNCHER ...

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

    4. VAL PARTIAL ELEVATION SHOWING LAUNCHER BRIDGE ON SUPPORTS, LAUNCHER SLAB, SUPPORT CARRIAGE, CONCRETE 'A' FRAME STRUCTURE AND CAMERA TOWER LOOKING SOUTHEAST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  6. Centrifugal projectile launchers

    NASA Astrophysics Data System (ADS)

    Felber, F. S.

    1982-01-01

    The concept of a centrifugal projectile launcher as an alternative to both chemical and electromagnetic launchers for anti-tank and air defence systems is discussed. It is shown that centrifugal projectile launchers can provide reliable, efficient, compact systems that will accelerate projectiles to 2-3 km/s with energies up to one megajoule. State-of-the-art composite rotors can be modified to launch projectiles of tens of grams to the order of 1 km/s. A demonstration rotor with reasonable energy density can be designed to accelerate 60 gram projectiles to 3 km/s repetitively.

  7. Superconducting Magnetic Projectile Launcher

    NASA Technical Reports Server (NTRS)

    Jan, Darrell L.; Lawson, Daniel D.

    1991-01-01

    Proposed projectile launcher exploits Meissner effect to transfer much of kinetic energy of relatively massive superconducting plunger to smaller projectile, accelerating projectile to high speed. Because it operates with magnetic fields, launcher not limited by gas-expansion thermodynamics. Plunger energized mechanically and/or chemically, avoiding need for large electrical power supplies and energy-storage systems. Potential applications include launching of projectiles for military purposes and for scientific and industrial tests of hypervelocity impacts.

  8. Stacked Buoyant Payload Launcher

    DTIC Science & Technology

    2013-05-14

    reserved for undersea launched missiles. Underwater deployment of smaller payloads has been limited to ejection from torpedo tubes, the trash disposal...COVERED 00-00-2014 to 00-00-2014 4. TITLE AND SUBTITLE Stacked Buoyant Payload Launcher 5a. CONTRACT NUMBER 5b. GRANT NUMBER 5c. PROGRAM...1 of 11 STACKED BUOYANT PAYLOAD LAUNCHER STATEMENT OF GOVERNMENT INTEREST [0001] The invention described herein may be manufactured and

  9. Characterization of the Ignition Over-Pressure/Sound Suppression Water in the Space Launch System Mobile Launcher Using Volume of Fluid Modeling

    NASA Technical Reports Server (NTRS)

    West, Jeff

    2015-01-01

    The Space Launch System (SLS) Vehicle consists of a Core Stage with four RS-25 engines and two Solid Rocket Boosters (SRBs). This vehicle is launched from the Launchpad using a Mobile Launcher (ML) which supports the SLS vehicle until its liftoff from the ML under its own power. The combination of the four RS-25 engines and two SRBs generate a significant Ignition Over-Pressure (IOP) and Acoustic Sound environment. One of the mitigations of these environments is the Ignition Over-Pressure/Sound Suppression (IOP/SS) subsystem installed on the ML. This system consists of six water nozzles located parallel to and 24 inches downstream of each SRB nozzle exit plane as well as 16 water nozzles located parallel to and 53 inches downstream of the RS-25 nozzle exit plane. During launch of the SLS vehicle, water is ejected through each water nozzle to reduce the intensity of the transient pressure environment imposed upon the SLS vehicle. While required for the mitigation of the transient pressure environment on the SLS vehicle, the IOP/SS subsystem interacts (possibly adversely) with other systems located on the Launch Pad. One of the other systems that the IOP/SS water is anticipated to interact with is the Hydrogen Burn-Off Igniter System (HBOI). The HBOI system's purpose is to ignite the unburned hydrogen/air mixture that develops in and around the nozzle of the RS-25 engines during engine start. Due to the close proximity of the water system to the HBOI system, the presence of the IOP/SS may degrade the effectiveness of the HBOI system. Another system that the IOP/SS water may interact with adversely is the RS-25 engine nozzles and the SRB nozzles. The adverse interaction anticipated is the wetting, to a significant degree, of the RS-25 nozzles resulting in substantial weight of ice forming and water present to a significant degree upstream of the SRB nozzle exit plane inside the nozzle itself, posing significant additional blockage of the effluent that exits the nozzle

  10. History of Indian launchers

    NASA Astrophysics Data System (ADS)

    Suresh, B. N.

    2008-07-01

    A multitude of inter-disciplinary technologies have been mastered indigenously for realizing a series of operational space launch vehicles. The vehicles range from relatively tiny Rohini sounding rockets to gigantic satellite launchers, PSLV and GSLV. This paper gives the challenges faced, lessons learned during various development phases and the step-by-step evolution of launch vehicle technologies in India.

  11. KENNEDY SPACE CENTER, FLA. - Workers, covered in protective clothing and breathing apparatus, continue sandblasting on the Mobile Launcher Platform on Launch Pad 39A to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

    NASA Image and Video Library

    2003-09-12

    KENNEDY SPACE CENTER, FLA. - Workers, covered in protective clothing and breathing apparatus, continue sandblasting on the Mobile Launcher Platform on Launch Pad 39A to remove corrosion before repainting. Routine maintenance includes sandblasting and repainting as preventive means to minimize corrosion.

  12. KENNEDY SPACE CENTER, FLA. - The camera installed on the aft skirt of a solid rocket booster is seen here, framed by the railing. The installation is in preparation for a vibration test of the Mobile Launcher Platform with SRBs and external tank mounted. The MLP will roll from one bay to another in the Vehicle Assembly Building.

    NASA Image and Video Library

    2003-11-06

    KENNEDY SPACE CENTER, FLA. - The camera installed on the aft skirt of a solid rocket booster is seen here, framed by the railing. The installation is in preparation for a vibration test of the Mobile Launcher Platform with SRBs and external tank mounted. The MLP will roll from one bay to another in the Vehicle Assembly Building.

  13. KENNEDY SPACE CENTER, FLA. - A camera is installed on the aft skirt of a solid rocket booster in preparation for a vibration test of the Mobile Launcher Platform with SRBs and external tank mounted. The MLP will roll from one bay to another in the Vehicle Assembly Building.

    NASA Image and Video Library

    2003-11-06

    KENNEDY SPACE CENTER, FLA. - A camera is installed on the aft skirt of a solid rocket booster in preparation for a vibration test of the Mobile Launcher Platform with SRBs and external tank mounted. The MLP will roll from one bay to another in the Vehicle Assembly Building.

  14. Rocket launchers as passive controllers

    NASA Astrophysics Data System (ADS)

    Cochran, J. E., Jr.; Gunnels, R. T.; McCutchen, R. K., Jr.

    1981-12-01

    A concept is advanced for using the motion of launchers of a free-flight launcher/rocket system which is caused by random imperfections of the rockets launched from it to reduce the total error caused by the imperfections. This concept is called 'passive launcher control' because no feedback is generated by an active energy source after an error is sensed; only the feedback inherent in the launcher/rocket interaction is used. Relatively simple launcher models with two degrees of freedom, pitch and yaw, were used in conjunction with a more detailed, variable-mass model in a digital simulation code to obtain rocket trajectories with and without thrust misalignment and dynamic imbalance. Angular deviations of rocket velocities and linear deviations of the positions of rocket centers of mass at burnout were computed for cases in which the launcher was allowed to move ('flexible' launcher) and was constrained so that it did not rotate ('rigid' launcher) and ratios of flexible to rigid deviations were determined. Curves of these error ratios versus launcher frequency are presented. These show that a launcher which has a transverse moment of inertia about its pivot point of the same magnitude as that of the centroidal transverse moments of inertia of the rockets launched from it can be tuned to passively reduce the errors caused by rocket imperfections.

  15. Coilgun Launcher for Nanosatellites

    SciTech Connect

    Turman, B.N.

    1999-03-23

    Nanosatellite space launches could significantly benefit from an electrically powered launch complex, based on an electromagnetic coil launcher. This paper presents results of studies to estimate the required launcher parameters and some fixed facility issues. This study is based on electromagnetic launch, or electromagnetic gun technology, which is constrained to a coaxial geometry to take advantage of the efficiency of closely-coupled coils. A baseline configuration for analysis considers a payload mass of 10 kg, launch velocity of 6 km/s, a second stage solid booster for orbital insertion, and a payload fraction of about 0.1. The launch facility is envisioned as an inclined track, 1-2 km in length, mounted on a hillside at 25 degrees aimed in the orbital inclination of interest. The launcher energy and power requirements fall in the range of 2000 MJ and 2 MW electric. This energy would be supplied by 400 modules of energy storage and magnetic coils. With a prime power generator of 2 MW, a launch rate of some 200 satellites per day is possible. The launch requires high acceleration, so the satellite package must be hardened to launch acceleration on the order of 1000 gee. Parametric evaluations compare performance parameters for a launcher length of 1-2 km, exit velocity of 4-8 km/s, and payloads of 1-100 kg. The EM launch complex could greatly reduce the amount of fuels handling, reduce the turn-around time between launches, allow more concurrence in launch preparation, reduce the manpower requirements for launch vehicle preparation and increase the reliability of launch by using more standardized vehicle preparations. Most importantly, such a facility could reduce the cost per launch and could give true launch-on-demand capability for nanosatellites.

  16. Air-Powered Projectile Launcher

    NASA Technical Reports Server (NTRS)

    Andrews, T.; Bjorklund, R. A.; Elliott, D. G.; Jones, L. K.

    1987-01-01

    Air-powered launcher fires plastic projectiles without using explosive propellants. Does not generate high temperatures. Launcher developed for combat training for U.S. Army. With reservoir pressurized, air launcher ready to fire. When pilot valve opened, sleeve (main valve) moves to rear. Projectile rapidly propelled through barrel, pushed by air from reservoir. Potential applications in seismic measurements, avalanche control, and testing impact resistance of windshields on vehicles.

  17. Air-Powered Projectile Launcher

    NASA Technical Reports Server (NTRS)

    Andrews, T.; Bjorklund, R. A.; Elliott, D. G.; Jones, L. K.

    1987-01-01

    Air-powered launcher fires plastic projectiles without using explosive propellants. Does not generate high temperatures. Launcher developed for combat training for U.S. Army. With reservoir pressurized, air launcher ready to fire. When pilot valve opened, sleeve (main valve) moves to rear. Projectile rapidly propelled through barrel, pushed by air from reservoir. Potential applications in seismic measurements, avalanche control, and testing impact resistance of windshields on vehicles.

  18. Rocket/launcher structural dynamics

    NASA Technical Reports Server (NTRS)

    Ferragut, N. J.

    1976-01-01

    The equations of motion describing the interactions between a rocket and a launcher were derived using Lagrange's Equation. A rocket launching was simulated. The motions of both the rocket and the launcher can be considered in detail. The model contains flexible elements and rigid elements. The rigid elements (masses) were judiciously utilized to simplify the derivation of the equations. The advantages of simultaneous shoe release were illustrated. Also, the loading history of the interstage structure of a boosted configuration was determined. The equations shown in this analysis could be used as a design tool during the modification of old launchers and the design of new launchers.

  19. Magnetic reconnection launcher

    DOEpatents

    Cowan, M.

    1987-04-06

    An electromagnetic launcher includes a plurality of electrical stages which are energized sequentially in the launcher with the passage of a projectiles. Each stage of the launcher includes two or more coils which are arranged coaxially on either closed-loop or straight lines to form gaps between their ends. The projectile has an electrically conductive gap-portion that passes through all the gaps of all the stages in a direction transverse to the axes of the coils. The coils receive an electric current, store magnetic energy, and convert a significant portion of the stored magnetic energy into kinetic energy of the projectile moves through the gap. The magnetic polarity of the opposing coils is in the same direction, e.g. N-S-N-S. A gap portion of the projectile may be made from aluminum and is propelled by the reconnection of magnetic flux stored in the coils which causes accelerating forces to act upon the projectile and at the horizontal surfaces of the projectile near its rear. The gap portion of the projectile may be flat, rectangular and longer than the length of the opposing coils. The gap portion of the projectile permits substantially unrestricted distribution of the induced currents so that current densities are only high where the useful magnetic force is high. This allows designs which permit ohmic oblation from the rear surfaces of the gap portion of the projectile allowing much high velocities to be achieved. An electric power apparatus controls the electric power supplied to the opposing coils until the gap portion of the projectile substantially occupies the gap between the coils, at which time the coils are supplied with peak current quickly. 8 figs.

  20. Electromagnetic Meissner effect launcher

    NASA Technical Reports Server (NTRS)

    Robertson, Glen A. (Inventor)

    1991-01-01

    An electromagnetic projectile launcher provides acceleration of a superconducting projectile through the diamagnetic repulsion of the superconducting projectile. A superconducting layer is provided aft of the projectile, either directly on the projectile or on a platform upon which the projectile is carried, and a traveling magnetic field is caused to propagate along a magnetic field drive coil in which the projectile is disposed. The resulting diamagnetic repulsion between the superconducting projectile and the traveling magnetic field causes the projectile to be propelled along the coil. In one embodiment, a segmented drive coil is used to generate the traveling magnetic field.

  1. Magnetic reconnection launcher

    DOEpatents

    Cowan, Maynard

    1989-01-01

    An electromagnetic launcher includes a plurality of electrical stages which are energized sequentially in synchrony with the passage of a projectile. Each stage of the launcher includes two or more coils which are arranged coaxially on either closed-loop or straight lines to form gaps between their ends. The projectile has an electrically conductive gap-portion that passes through all the gaps of all the stages in a direction transverse to the axes of the coils. The coils receive an electric current, store magnetic energy, and convert a significant portion of the stored magnetic energy into kinetic energy of the projectile by magnetic reconnection as the gap portion of the projectile moves through the gap. The magnetic polarity of the opposing coils is in the same direction, e.g. N-S-N-S. A gap portion of the projectile may be made from aluminum and is propelled by the reconnection of magnetic flux stored in the coils which causes accelerating forces to act upon the projectile at both the rear vertical surface of the projectile and at the horizontal surfaces of the projectile near its rear. The gap portion of the projectile may be flat, rectangular and longer than the length of the opposing coils and fit loosely within the gap between the opposing coils.

  2. Magnetic reconnection launcher

    SciTech Connect

    Cowan, M.

    1989-04-04

    An electromagnetic launcher is described, which includes a plurality of electrical stages which are energized sequentially in synchrony with the passage of a projectile. Each stage of the launcher includes two or more coils which are arranged coaxially on either closed-loop or straight lines to form gaps between their ends. The projectile has an electrically conductive gap-portion that passes through all the gaps of all the stages in a direction transverse to the axes of the coils. The coils receive an electric current, store magnetic energy, and convert a significant portion of the stored magnetic energy into kinetic energy of the projectile by magnetic reconnection as the gap portion of the projectile moves through the gap. The magnetic polarity of the opposing coils is in the same direction, e.g. N-S-N-S. A gap portion of the projectile may be made from aluminum and is propelled by the reconnection of magnetic flux stored in the coils which causes accelerating forces to act upon the projectile at both the rear vertical surface of the projectile and at the horizontal surfaces of the projectile near its rear. The gap portion of the projectile may be flat, rectangular and longer than the length of the opposing coils and fit loosely within the gap between the opposing coils.

  3. Kinetic model of phase separation in binary mixtures with hard mobile impurities.

    PubMed

    Ginzburg, V V; Peng, G; Qiu, F; Jasnow, D; Balazs, A C

    1999-10-01

    We develop a mean-field rate-equation model for the kinetics of phase separation in binary mixtures with hard mobile impurities. For impurities preferentially wet by one of the components, the phase separation is arrested in the late stage. The "steady-state" domain size depends strongly on both the particle diffusion constant and the particle concentration. We compare theoretical results with the simulation data and find good qualitative agreement.

  4. The SHARP scramjet launcher

    SciTech Connect

    Cartland, H.; Fiske, P.; Greenwood, R.; Hargiss, D.; Heston, P.; Hinsey, N.; Hunter, J.; Massey, W.

    1995-01-10

    The worlds largest light gas gun at SHARP (Super High Altitude Research Project) is completed and in the past year has launched 9 scramjets. Typical masses and velocities are 5.9 kg at 2.8 km/sec.and 4.4 kg at 3.1 km/sec. In so doing SHARP launched the first fully functioning, hydrogen burning scramjet at mach 8. The SHARP launcher is unique in having a 4 inch diameter and 155 foot-long barrel. This enables lower acceleration launches than any other system. In addition the facility can deliver high energy projectiles to targets in the open air without having to contain the impact fragments. This allows one to track lethality test debris for several thousand feet.

  5. Does Mobility Have to Mean Being Hard to Reach? Mobile Pastoralists and Education's "Terms of Inclusion"

    ERIC Educational Resources Information Center

    Dyer, Caroline

    2013-01-01

    Nomadic groups are highly discriminated against in access to education services, and the 2010 Education For All Global Monitoring Report demanded urgent action to address their education deprivation. Mobile pastoralists, particularly, appear to be falling beyond the remit of migration studies in education, although they are among the most mobile…

  6. Vehicle Concept for a Robotic Missile Launcher.

    DTIC Science & Technology

    1983-05-01

    Co-rc AH0-3P00 aan Mr alD ern q~LL. BE eor N .30-0 C. F8NA 05OR C~ntact AAH~-33--0W0 T44 BUREAU OF ENGINEERING RESEARCH Members of the...in the development of its graduate program, the College recognized that men and women engaged in research should be as free as possible of the...several vehicular components. Existing missile launchers are to be mounted on highly mobile, unmanned vehicles to be remotely controlled from a manned

  7. Historic and Current Launcher Success Rates

    NASA Technical Reports Server (NTRS)

    Rust, Randy

    2002-01-01

    This presentation reviews historic and current space launcher success rates from all nations with a mature launcher industry. Data from the 1950's through present day is reviewed for possible trends such as when in the launch timeline a failure occurred, which stages had the highest failure rate, overall launcher reliability, a decade by decade look at launcher reliability, when in a launchers history did failures occur, and the reliability of United States human-rated launchers. This information is useful in determining where launcher reliability can be improved and where additional measures for crew survival (i.e., Crew Escape systems) will have the greatest emphasis

  8. The DSI small satellite launcher

    NASA Technical Reports Server (NTRS)

    Nichols, S.; Gibbons, D.; Wise, J.; Nguyen, D.

    1992-01-01

    A new launcher has been developed by DSI, that is compatible with the GAS canisters. It has the proven capability to deploy a satellite from an orbiting Shuttle that is 18 inches in diameter, 31 inches long, and weighing 190 pounds. These DSI Launchers were used aboard the Discovery (STS-39) in May 1991 as part of the Infrared Background Signature Survey (IBSS) to deploy three small satellites known as Chemical Release Observation (CRO) satellites A, B, and C. Because the satellites contained hazardous liquids (MMH, UDMH, and MON-10) and were launched from GAS Cylinders without motorized doors, the launchers were required to pass NASA Shuttle Payload safety and verification requirements. Some of the more interesting components of the design were the V-band retention and separation mechanism, the separation springs, and the launcher electronics which provided a properly inhibited release sequence operated through the Small Payload Accommodations Switch Panel (SPASP) on board the Orbiter. The original plan for this launcher was to use a motorized door. The launcher electronics, therefore has the capability to be modified to accommodate the door, if desired.

  9. Association of limited joint mobility and increased plantar hardness in diabetic foot ulceration in north Asian Indian: a preliminary study.

    PubMed

    Periyasamy, R; Anand, Sneh; Ammini, A C

    2012-04-01

    The aim of this article is to investigate the association of limited joint mobility and foot sole hardness in north Asian Indian type 2 diabetic patients. Limited joint mobility and hardness of the foot sole were measured for 39 subjects attending the AIIMS Endocrinology & Metabolism Clinic. The total subject divided into three groups: 13 control subjects (nondiabetic), 13 diabetic patients without neuropathy and 13 diabetic neuropathy patients. Neuropathy status was assessed using 10 gm Semen's Weinstein monofilament. Joint mobility parameters, such as ankle dorsiflexion/plantar flexion and metatarsophalangeal-1 dorsiflexion/plantar flexion, are measured using a goniometer. Foot sole hardness was measured using a durometer or shore meter. We found that diabetic patients with a neuropathic foot had significantly reduced joint mobility and increased foot sole hardness, placing them at risk for subsequent ulceration. Metatarsophalangeal-1 dorsiflexion/plantar flexion of both feet of diabetic patients had significant correlation (at p < 0.05, p < 0.001, p < 0.001 level) over age and body mass index. Also ankle plantar flexion/dorsiflexion and metatarsophalangeal-1 dorsiflexion/plantar flexion has a significant correlations (at p < 0.01, p < 0.05, p < 0.001, p < 0.001 level) with foot sole hardness in both feet of diabetic neuropathy subjects. Also linear regression analysis showed that duration of diabetes was significantly associated with the joint mobility parameters. In this study we conclude that joint mobility had reduced further if neuropathy and increased foot sole hardness coexisted owing to high plantar pressures. Hence, both limited joint mobility and increased foot sole hardness appears to be important determinants of foot sole ulceration in diabetic neuropathic subject.

  10. Induction generator powered coaxial launchers

    SciTech Connect

    Nalty, K.E.; Driga, M.D. . Dept. of Electrical and Computer Engineering)

    1991-01-01

    Most coaxial accelerator concepts to date have used switched power supplies to energize coils in the vicinity of the projectile, or have tolerated a grossly oversized power supply which energizes all coils during the course of the launch. Coordination of the switching, while engineeringly possible, provides opportunities for failure which reduces the reliability of the system as compared to a passively activated system requiring no switching. Excitation of un-used sections of a launcher dramatically reduces launch efficiency, and increases both power supply and cooling requirements. A launcher design which avoids the need for switching and automatically excites only the windings in the vicinity of the projectile is presented in this paper. The energy store for the launcher consists of rotating induction machines. The excitation for the launcher is provided by an excitation winding on the projectile, which makes the projectile act like the rotor of a synchronous condenser. This combination of super-synchronous induction machines (the energy stores) and synchronous alternators (the projectile) is called an induction generator. This paper provides a description of the induction generator powered launcher concept, and investigates scaling laws to assess the applicability of this technology for tactical and space launch applications.

  11. MULTIPLE ECH LAUNCHER CONTROL SYSTEM

    SciTech Connect

    GREEN,M.T; PONCE,D; GRUNLOH,H.J; ELLIS,R.A; GROSNICKLE,W.H; HUMPHREY,R.L

    2003-10-01

    OAK-B135 The addition of new, high power gyrotrons to the heating and current drive arsenal at DIII-D, required a system upgrade for control of fully steerable ECH Launchers. Each launcher contains two pointing mirrors with two degrees of mechanical freedom. The two flavors of motion are called facet and tilt. Therefore up to four channels of motion per launcher need to be controlled. The system utilizes absolute encoders to indicate mirror position and therefore direction of the microwave beam. The launcher movement is primarily controlled by PLC, but future iterations of design, may require this control to be accomplished by a CPU on fast bus such as Compact PCI. This will be necessary to accomplish real time position control. Safety of equipment and personnel is of primary importance when controlling a system of moving parts. Therefore multiple interlocks and fault status enunciators have been implemented. This paper addresses the design of a Multiple ECH Launcher Control System, and characterizes the flexibility needed to upgrade to a real time position control system in the future.

  12. 32. VAL, DETAIL SHOWING LOADING PLATFORM, PROJECTILE LOADING CAR, LAUNCHER ...

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

    32. VAL, DETAIL SHOWING LOADING PLATFORM, PROJECTILE LOADING CAR, LAUNCHER SLAB AND UNDERSIDE OF LAUNCHER BRIDGE LOOKING SOUTHWEST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  13. 21. VAL, DETAIL OF MUZZLE END OF LAUNCHER BRIDGE SHOWING ...

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

    21. VAL, DETAIL OF MUZZLE END OF LAUNCHER BRIDGE SHOWING BOTH LAUNCHER TUBES TAKEN FROM RESERVOIR LOOKING NORTH. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  14. Space transportation propulsion USSR launcher technology, 1990

    NASA Technical Reports Server (NTRS)

    1991-01-01

    Space transportation propulsion U.S.S.R. launcher technology is discussed. The following subject areas are covered: Energia background (launch vehicle summary, Soviet launcher family) and Energia propulsion characteristics (booster propulsion, core propulsion, and growth capability).

  15. 89. 22'X34' original vellum, VariableAngle Launcher 'ELEVATION OF LAUNCHER BRIDGE ...

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

    89. 22'X34' original vellum, Variable-Angle Launcher 'ELEVATION OF LAUNCHER BRIDGE ON TEMPORARY SUPPORT' drawn at 1'=20'. (BUORD Sketch # 209786, PAPW 1932). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  16. 90. 22'X34' original blueprint, VariableAngle Launcher, 'FRONT ELEVATION OF LAUNCHER ...

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

    90. 22'X34' original blueprint, Variable-Angle Launcher, 'FRONT ELEVATION OF LAUNCHER BRIDGE, CONNECTING BRIDGE AND BARGES' drawn at 1/4'=1'0'. (BUROD Sketch # 208247). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  17. Teaching Math to Deaf/Hard-of-Hearing (DHH) Children Using Mobile Games: Outcomes with Student and Teacher Perspectives

    ERIC Educational Resources Information Center

    Shelton, Brett E.; Parlin, Mary Ann

    2016-01-01

    Leveraging the use of mobile devices for education, such as instructional games, is an area of increasing interest for targeted subpopulations of students including those who are deaf/hard-of-hearing (DHH). This paper outlines the perspectives of Deaf Education teachers and DHH children who participated in the GeePerS*Math project. Interviews and…

  18. Electromagnetic launchers for space applications

    NASA Technical Reports Server (NTRS)

    Schroeder, J. M.; Gully, J. H.; Driga, M. D.

    1989-01-01

    An electromagnetic launcher (EML) was designed for NASA-Langley to boost large models to hypervelocity for flight evaluation. Two different concepts were developed using railgun and coilgun principles. A coilgun was designed to accelerate a 14-kg mass to 6 km/s and, by adding additional equipment, to accelerate a 10-kg mass to 11 km/s. The railgun system was designed to accelerate only 14 kg to 6 km/s. Of significance in this development is the opportunity to use the launcher for aeroballistic research of the upper atmosphere, eventually placing packages in low earth orbit using a small rocket. The authors describe the railgun and coilgun launch designs and suggest a reconfiguration for placement of 150-kg parcels into low earth orbit for aeroballistic studies and possible space lab support. Each design is detailed along with the performance adjustments which would be required for circular orbit payload placement.

  19. Electromagnetic launchers for space applications

    NASA Technical Reports Server (NTRS)

    Schroeder, J. M.; Gully, J. H.; Driga, M. D.

    1989-01-01

    An electromagnetic launcher (EML) was designed for NASA-Langley to boost large models to hypervelocity for flight evaluation. Two different concepts were developed using railgun and coilgun principles. A coilgun was designed to accelerate a 14-kg mass to 6 km/s and, by adding additional equipment, to accelerate a 10-kg mass to 11 km/s. The railgun system was designed to accelerate only 14 kg to 6 km/s. Of significance in this development is the opportunity to use the launcher for aeroballistic research of the upper atmosphere, eventually placing packages in low earth orbit using a small rocket. The authors describe the railgun and coilgun launch designs and suggest a reconfiguration for placement of 150-kg parcels into low earth orbit for aeroballistic studies and possible space lab support. Each design is detailed along with the performance adjustments which would be required for circular orbit payload placement.

  20. Electromagnetic Meissner-Effect Launcher

    NASA Technical Reports Server (NTRS)

    Robertson, Glen A.

    1990-01-01

    Proposed electromagnetic Meissner-effect launching apparatus differs from previous electromagnetic launchers; no need for electromagnet coil on projectile. Result, no need for brush contacts and high-voltage commutation equipment to supply current directly to projectile coil, or for pulse circuitry to induce current in projectile coil if brush contacts not used. Compresses magnetic field surrounding rear surface of projectile, creating gradient of magnetic pressure pushing projectile forward.

  1. A multiple armature railgun launcher

    NASA Astrophysics Data System (ADS)

    Challita, Antonios; Maas, Brian L.; Bauer, David P.; Heyse, Mark

    1993-01-01

    Railgun launchers with multiple armatures, which can distribute the accelerating force on the projectile, supply each armature with gun current for acceleration through its own set of rails. Test results are reported which confirm the feasibility of this concept; it is shown that the control of current distribution to multiple armatures is possible. Attention is given to gun behavior for the case of high length/diameter projectiles.

  2. Electromagnetic Meissner-Effect Launcher

    NASA Technical Reports Server (NTRS)

    Robertson, Glen A.

    1990-01-01

    Proposed electromagnetic Meissner-effect launching apparatus differs from previous electromagnetic launchers; no need for electromagnet coil on projectile. Result, no need for brush contacts and high-voltage commutation equipment to supply current directly to projectile coil, or for pulse circuitry to induce current in projectile coil if brush contacts not used. Compresses magnetic field surrounding rear surface of projectile, creating gradient of magnetic pressure pushing projectile forward.

  3. Traveling-wave induction launchers

    NASA Technical Reports Server (NTRS)

    Elliott, David G.

    1989-01-01

    An analysis of traveling-wave induction launchers shows that induction is a feasible method of producing armature current and that efficient accelerators can be built without sliding contacts or arcs. In a traveling-wave induction launcher the armature current is induced by a slip speed between the armature and a traveling magnetic field. At 9 m/s slip speed a 9 kg projectile with an aluminum armature weighing 25 percent of the total mass can be accelerated to 3000 m/s in a 5 m-long barrel with a total ohmic loss in the barrel coils and armature of 4 percent of the launch kinetic energy and with an average armature temperature rise of 220 deg C, but a peak excitation frequency of 8600 Hz is required. With a 2 kg launch mass the ohmic loss is 7 percent. A launcher system optimized for rotating generators would have a peak frequency of 4850 Hz; with an aluminum armature weighing 33 percent of the launch mass and a slip speed of 30 m/s the total ohmic loss in the generators, cables, and accelerator would be 43 percent of the launch kinetic energy, and the average armature temperature rise would be 510 deg C.

  4. Mobile hard substrata - An additional biodiversity source in a high latitude shallow subtidal system

    NASA Astrophysics Data System (ADS)

    Balazy, Piotr; Kuklinski, Piotr

    2013-03-01

    This study demonstrates the importance of a hard mobile substratum (hermit crab shells) for Arctic biodiversity. Based on previous observations from other geographic regions we hypothesized that this niche at high latitudes would support a higher biodiversity of epifauna than might be predicted from similar substrata. We test whether the hermit crab epifauna is specific to that substratum providing unique biodiversity components to the local community. From four study sites in Isfjorden (78°N), West Spitsbergen and two study sites in Northern Norway (69°N) we collected approximately 50 each of hermit crabs, gastropods and pebbles, of visually similar surface area using SCUBA diving. Hermit crab shells were colonized by a larger number of epifaunal species than either gastropods or pebbles, even when they were of a larger size. Among 87 taxa found on all the three substrata, 22 occurred only on hermit crab shells. Except for two study sites hermit crab shells also supported more individuals. This study shows that the contribution of shells carried by hermit crabs to high-latitude, shallow-subtidal diversity is higher than might be predicted by their surface area alone and that hermit crabs modify, maintain and create a unique habitat. This is the result of a number of factors interacting positively on the presence of epifauna including shell surface heterogeneity and the complex influence of the crab host.

  5. An electomagnetic lunar launcher utilizing superconductivity technology

    NASA Technical Reports Server (NTRS)

    Bilby, Curt; Nozette, Stewart; Kolm, Henry

    1989-01-01

    The application of superconductivity technology to the lunar launcher problem was considered, and a quenchgun concept was formulated to reduce the mass of the launcher system by incorporating the energy storage in the launcher itself and using the efficiency of the quenchgun to reduce the power requirements. A conceptual design for the quenchgun launcher is presented, and the integration of the system into a lunar base logistics model for evaluation is addressed. The results of these evaluations under the NASA Office of Exploration lunar base scenarios are reported.

  6. A 10-stage reconnection demonstration launcher

    SciTech Connect

    Cnare, E.C.; Widner, M.M.; Duggin, B.W.

    1989-01-01

    A small-scale, 10-stage cylindrical reconnection launcher has been designed, fabricated, and tested. Ten-gram projectiles are accelerated from rest to 317 m/s through the 0.44 m launcher assembly with a projectile kinetic energy to capacitor stored energy efficiency of 9%. Comparison of test results and computer code predictions will be presented. Results of these studies have substantiated launcher scaling at small size and have provided a useful test bed for launcher components and diagnostics. 5 refs., 6 figs.

  7. A 10-stage reconnection demonstration launcher

    SciTech Connect

    Cnare, E.G.; Widner, M.M.; Duggins, B.W. )

    1991-01-01

    This paper reports on a small-scale, 10-stage cylindrical reconnection launcher that has been designed, fabricated, and tested. Ten-gram projectiles are accelerated from rest to 317 m/s through the 0.44 m launcher assembly with a projectile kinetic energy to capacitor stored energy efficiency of 9%. Comparison of test results and computer code predictions are presented. Results of these studies have substantiated launcher scaling at small size and have provided a useful test bed for launcher components and diagnostics.

  8. 17. VAL PROJECTILE LOADING DECK AND BREECH END OF LAUNCHER ...

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

    17. VAL PROJECTILE LOADING DECK AND BREECH END OF LAUNCHER BRIDGE LOOKING SOUTH. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  9. 1. VARIABLEANGLE LAUNCHER (VAL) CONCRETE 'A' FRAME STRUCTURE SHOWING CAMERA ...

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

    1. VARIABLE-ANGLE LAUNCHER (VAL) CONCRETE 'A' FRAME STRUCTURE SHOWING CAMERA TOWER STRUCTURE LOOKING SOUTH AND ARCHED OPENING FOR ROADWAY. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  10. 48. VIEW ACROSS RESERVOIR OF SLOPE PREPARATION FOR VARIABLEANGLE LAUNCHER ...

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

    48. VIEW ACROSS RESERVOIR OF SLOPE PREPARATION FOR VARIABLE-ANGLE LAUNCHER (VAL) SLAB LOOKING NORTHEAST, November 6, 1946. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  11. 46. VAL, DETAIL OF 'PILLOW BLOCK' WHERE LAUNCHER BRIDGE PIN ...

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

    46. VAL, DETAIL OF 'PILLOW BLOCK' WHERE LAUNCHER BRIDGE PIN SAT AT THE TOP OF THE CONNECTING BRIDGE. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  12. 25. VAL, DETAIL OF CONTROL PANEL FOR LAUNCHER BRIDGE, COUNTERWEIGHT ...

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

    25. VAL, DETAIL OF CONTROL PANEL FOR LAUNCHER BRIDGE, COUNTERWEIGHT CAR AND WINDSTAY WINCHES. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  13. 24. VAL, CONTROL PANELS FOR LAUNCHER BRIDGE COUNTERWEIGHT CAR AND ...

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

    24. VAL, CONTROL PANELS FOR LAUNCHER BRIDGE COUNTERWEIGHT CAR AND WINDSTAY WINCHES OVERLOOKING FIRING RANGE AND MORRIS DAM LOOKING SOUTHWEST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  14. 31. VAL, DETAIL OF LOADING PLATFORM ADJACENT TO LAUNCHER BRIDGE ...

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

    31. VAL, DETAIL OF LOADING PLATFORM ADJACENT TO LAUNCHER BRIDGE LOOKING WEST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  15. 6. VAL LAUNCHER BRIDGE, CARRIAGE SUPPORT, CONCRETE 'A' FRAME STRUCTURE ...

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

    6. VAL LAUNCHER BRIDGE, CARRIAGE SUPPORT, CONCRETE 'A' FRAME STRUCTURE AND CAMERA TOWER LOOKING NORTHWEST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  16. 18. VAL, DETAIL OF LAUNCHER BRIDGE ALONG THE SIDE OF ...

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

    18. VAL, DETAIL OF LAUNCHER BRIDGE ALONG THE SIDE OF THE 32' DIAMETER LAUNCHING TUBE LOOKING SOUTHWEST. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  17. 26. VAL, DETAIL OF CONTROL PANEL FOR LAUNCHER BRIDGE, COUNTERWEIGHT ...

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

    26. VAL, DETAIL OF CONTROL PANEL FOR LAUNCHER BRIDGE, COUNTERWEIGHT CAR AND WINDSTAY WINCHES. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  18. 49. DETAIL VIEW OF SLOPE PREPARATION FOR VARIABLEANGLE LAUNCHER SLAB ...

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

    49. DETAIL VIEW OF SLOPE PREPARATION FOR VARIABLE-ANGLE LAUNCHER SLAB LOOKING NORTH, November 6, 1946. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  19. Winged launcher thermal design aspects

    NASA Astrophysics Data System (ADS)

    Keller, K.

    1991-12-01

    The need for significant reduction in launch cost favors the consideration of reusable space transportation systems which are assisted by aerodynamic lift. The thermomechanical and thermochemical environments and the basic design requirements of two airbreathing vehicle classes are put in relation to vehiles like Shuttle and Hermes. Similarities as well as essential differences between the various vehicles are highlighted. State of the art thermal protection concepts and materials are analyzed with respect to winged launcher concepts. Future development trends for design and materials with potential application are identified. The need for improved thermostructural analysis and optimization techniques is outlined.

  20. Hypervelocity Launcher for Aerothermodynamic Experiments. Phase 2

    NASA Technical Reports Server (NTRS)

    Scholz, Timothy J.; Bauer, David P.

    1995-01-01

    The capability of an Ultra Distributed Energy Store System (UDESS) powered electromagnetic launcher (EM) is experimentally assessed. The UDESS system was developed specifically to address the velocity speed limit seen in plasma armature EM launchers. Metal armature launch packages were also developed and tested to assess the usefulness of the UDESS concept for low velocity applications.

  1. Himass electromagnetic launcher at Los Alamos

    SciTech Connect

    Zimmermann, E.L.; Fowler, C.M.; Foley, E.; Parker, J.V.

    1986-01-01

    The HIMASS electromagnetic launcher is a unique large-bore, large-mass railgun driven by a helical flux compression generator. Two experiments were conducted at 3 to 4 MA current levels. The objective of the experiments was to study the effects of scaling, ablation, and material parameters on electromagnetic launcher performance. Data from these two experiments are presented.

  2. HIMASS electromagnetic launcher at Los Alamos

    SciTech Connect

    Zimmerman, E.L.; Fowler, C.M.; Foley, E.; Parker, J.V.

    1986-11-01

    The HIMASS electromagnetic launcher is a unique large-bore, large-mass railgun driven by a helical flux compression generator. Two experiments were conducted at 3-4 MA current levels. The objective of the experiments was to study the effects of scaling, ablation, and material parameters on electromagnetic launcher performance. Data from these two experiments are presented.

  3. 33 CFR 175.113 - Launchers.

    Code of Federal Regulations, 2010 CFR

    2010-07-01

    ... 33 Navigation and Navigable Waters 2 2010-07-01 2010-07-01 false Launchers. 175.113 Section 175.113 Navigation and Navigable Waters COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) BOATING SAFETY EQUIPMENT REQUIREMENTS Visual Distress Signals § 175.113 Launchers. (a) When a visual...

  4. Parameter studies for traveling wave coaxial launchers

    SciTech Connect

    Wu, A.Y. . Center for Electromechanics)

    1991-01-01

    The traveling wave coaxial launcher is a complex machine that requires very extensive parameter studies to optimize. Most of previous attempts to realize hypervelocity using coaxial launchers have failed partly due to inadequate analyses. This paper reports the results of very extensive air-core coaxial launcher parameter studies performed using computers. These results and the methodology introduced should help future researchers on this topic. In the course of studying the feasibility of accelerating a 1-kg projectile to 10 km/s with an 18 m air-core multiphase coaxial launcher powered by a rising frequency generator (RFGs), a complete simulation code based on the current filament method was developed. Results from the simulation code indicate rather chaotic behavior of an arbitrary coaxial launcher design. More fundamental studies were then conducted using various computer codes based on the current filament method.

  5. The enhanced ASDEX Upgrade pellet centrifuge launcher

    NASA Astrophysics Data System (ADS)

    Plöckl, B.; Lang, P. T.

    2013-10-01

    Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system. Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.

  6. The enhanced ASDEX Upgrade pellet centrifuge launcher.

    PubMed

    Plöckl, B; Lang, P T

    2013-10-01

    Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system. Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.

  7. The enhanced ASDEX Upgrade pellet centrifuge launcher

    SciTech Connect

    Plöckl, B.; Lang, P. T.

    2013-10-15

    Pellets played an important role in the program of ASDEX Upgrade serving both for investigations on efficient particle fuelling and high density scenarios but also for pioneering work on Edge Localised Mode (ELM) pacing and mitigation. Initially designed for launching fuelling pellets from the magnetic low field side, the system was converted already some time ago to inject pellets from the magnetic high field side as much higher fuelling efficiency was found using this configuration. In operation for more than 20 years, the pellet launching system had to undergo a major revision and upgrading, in particular of its control system. Furthermore, the control system installed adjacent to the launcher had to be transferred to a more distant location enforcing a complete galvanic separation from torus potential and a fully remote control solution. Changing from a hybrid system consisting of PLC S5/S7 and some hard wired relay control to a state of the art PLC system allowed the introduction of several new operational options enabling more flexibility in the pellet experiments. This article describes the new system architecture of control hardware and software, the operating procedure, and the extended operational window. First successful applications for ELM pacing and triggering studies are presented as well as utilization for the development of high density scenarios.

  8. Technology demonstration for reusable launchers

    NASA Astrophysics Data System (ADS)

    Baiocco, P.; Bonnal, Ch.

    2016-03-01

    Reusable launchers have been studied under CNES contracts for more than 30 years, with early concepts such as STS-2000 or Oriflamme, more recently with very significant efforts devoted to Liquid Fly Back Boosters as with the Bargouzin project led with Tsniimash, TSTO with the Everest concept studied by Airbus-DS as prime contractor or the RFS Reusable First Stage concept of a large first stage associated to a cryotechnic second stage. These investigations, summarized in the first part of the paper, enabled CNES to identify clearly the technology requirements associated to reusability, as well as cost efficiency through detailed non-recurring costs and mission costs analysis. In parallel, CNES set in place development logic for sub-systems and equipment based on demonstrators, hardware test benches enabling maturation of technologies up to a TRL such that an actual development can be decided with limited risk. This philosophy has been applied so far to a large number of cases, such as TPTech and TPX for Hydrogen turbo pump, GGPX as demonstrator of innovative gas generator, HX demonstrator of modern cryotechnic upper stage with a dozen of different objectives (Thermal Protection, 20K Helium storage, measurements …). This virtuous approach, "learn as you test", is currently applied in the phased approach towards scaled down reusable booster stage, whose possibility to be used as first stage of a microlaunch vehicle is under investigation. The selected technologies allow paving the way towards reusable booster stages for Ariane 6 evolutions or main reusable stage for a further generation of heavy launchers. The paper describes the logic behind this project, together with the demonstration objectives set for the various sub-systems as well as operations.

  9. 30. VAL LOOKING DOWN THE LAUNCHER SLAB STAIRS AT THE ...

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

    30. VAL LOOKING DOWN THE LAUNCHER SLAB STAIRS AT THE PROJECTILE LOADING CAR AND LOADING PLATFORM ADJACENT TO THE PROJECTILE LOADING DECK AND LAUNCHER BRIDGE. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  10. New developments in the field of launchers

    NASA Astrophysics Data System (ADS)

    Koelle, H. H.; Arend, H.

    The current status of launch-system technology is discussed in a global survey. Topics addressed include the factors influencing launcher cost effectiveness; the capabilities of state-of-the-art Soviet, U.S., European, Chinese, and Japanese systems; possible improvements to the current launchers; alternative technologies (the ESA Hermes shuttle, SSTO vehicles, etc.); and future trends in the commercial launch market. Particular attention is given to the Neptun two-stage reusable ballistic launcher proposed by Apel et al. (1985). It is suggested that it may be possible to lower specific transport costs to about $500/kg, or even to $100/kg if the lifetime cargo capacity of reusable launchers can be extended to the order of 2 Tg. Extensive diagrams, drawings, and tables of numerical data are provided.

  11. Study of new materials for railgun launchers

    SciTech Connect

    Poltanov, A.; Jygailo, N.; Bykov, M.; Glinov, A.; Svobodov, A.; Belyakov, A.; Chernetskaya, N.

    1997-01-01

    The description of new materials which can be used in railgun launchers is presented. Mo-W compositions in the Cu matrix, binary composites with anisotropic conductivity, ceramics and ceramic covers have been studied as materials for rails, solid armature and insulator respectively. The tests have been conducted on a 1m long railgun launcher with a section of the bore 10mm x 10mm using a current with the amplitude 350--400 kA. Main test results are demonstrated.

  12. Design of a high power TM01 mode launcher optimized for manufacturing by milling

    SciTech Connect

    Dal Forno, Massimo

    2016-12-15

    Recent research on high gradient rf acceleration found that hard metals, such as hard copper and hard coppersilver, have lower breakdown rate than soft metals. Traditional high gradient accelerating structures are manufactured with parts joined by high temperature brazing. The high temperature used in brazing makes the metal soft, therefore this process cannot be used to manufacture structures out of hard metal alloys. In order to build the structure with hard metals, the components must be designed for joining without high temperature brazing. One method is to build the accelerating structures out of two halves, and joining them by using a low temperature techniques, at the symmetry plane along the beam axis. The structure has input and output rf power couplers. We use a TM01 mode launcher as a rf power coupler, which was introduced during the Next Linear Collider (NLC) work. The part of the mode launcher will be built in each half of the structure. This paper presents a novel geometry of a mode launcher, optimized for manufacturing by milling. The coupler was designed for the CERN CLIC working frequency f = 11.9942 GHz; the same geometry can be scaled to any other frequency.

  13. The rise of the mobile phone in the hard drug scene of Rotterdam.

    PubMed

    Barendregt, Cas; van der Poel, Agnes; van de Mheen, Dike

    2006-03-01

    The rise of mobile phone dealing in the retail market of heroin and cocaine in the city of Rotterdam is described. Multiple methods were used for the study, including analysis of street survey data (1998, 2000, 2003), qualitative and quantitative analysis of fieldwork data, and semi-open interviews with drug users and key informants. In 2000, 70% of the respondents to a street survey bought drugs from a mobile dealer. Qualitative data showed that the majority of mobile dealers have an ethnic Moroccan background; the reasons for this may include the ambiguous attitude of the Moroccan community towards drug crime, and repressive legislation causing the market to find alternatives for basic street dealing. The rise of mobile dealing is discussed as a form of reshaping of the drug market under prohibition.

  14. A multiple armature railgun launcher

    NASA Astrophysics Data System (ADS)

    Heyse, Mark W.; Challita, Antonios; Maas, Brian L.; Bauer, David P.

    1993-01-01

    As longer projectiles are accelerated, the efficiency (projectile mass/launch mass) of the launch package decreases. The reduction in efficiency makes launching projectiles with a L/D (length-to-diameter ratio) greater than 20 undesirable. EM guns have several launch characteristics that differ from conventional guns. Higher launch velocities are achievable in EM guns because sonic gas velocities do not limit the projectile velocity. Acceleration profiles for EM guns are more constant. The acceleration forces can be distributed on the projectile easily because the accelerating force can be distributed with multiple armatures. These characteristics combine to make EN guns a very attractive approach for launching very long (i.e.. high L/D ratio) projectiles. Railgun launchers with multiple armatures can distribute the accelerating force. Each armature is supplied gun current for acceleration through its own set of rails. This multi-rail, multi-armature concept was tested at the railgun test facility. The results demonstrated feasibility. We were able to control current distribution to multiple armatures. This paper describes the theory and test results for multi-armature launch of high L/D projectiles.

  15. Performance of an induction coil launcher

    SciTech Connect

    Shokair, I.R.; Cowan, M.; Kaye, R.J.; Marder, B.M.

    1993-12-31

    Performance of an electromagnetic induction launcher is considered for three types of armatures. These are: Solid, 1-element wound and 16-element wound aluminum armatures. The one element wound armature has uniform current density throughout. Because of the uniformity of the current density, the wound armature can withstand field reversal and still maintain low temperature. Slingshot simulations were performed for several configurations. Best performance was obtained for a single element wound armature with two field reversals. For a 60 kg projectile, 10.5 cm coil inner radius and 5.5 cm coil build, the velocity after 50 meters of launcher length (670 stages) exceeded 3.5 km/sec with an overall efficiency of about 45%. For the same parameters the solid and 16-element wound armatures reach a velocity of about 3.3 km/sec after 800 stages (60 meters of launcher length) but without field reversal. A velocity of 3.5 km/sec is possible after 60 meters of launcher length with the 16-element wound armature with one field reversal, but the temperature is close to the melting temperature of aluminum. In all simulations with a solid armature, melting of some of the surface material occurs. However, it is shown that most of the melting occurs after contribution has been made to the forward going pressure, that is, melting does not affect the electrical performance of the launcher. The effect of coil firing time jitter on launcher performance is also considered and is found to be very small for realistic perturbations. For {plus_minus} 2 {mu}-secs random jitter, the reduction in the final velocity for a 60 meter launcher with a solid armature is less than 0.1% and the increase in temperature is only 2%. This result holds for all types of armatures.

  16. Distributed data fusion across multiple hard and soft mobile sensor platforms

    NASA Astrophysics Data System (ADS)

    Sinsley, Gregory

    is a younger field than centralized fusion. The main issues in distributed fusion that are addressed are distributed classification and distributed tracking. There are several well established methods for performing distributed fusion that are first reviewed. The chapter on distributed fusion concludes with a multiple unmanned vehicle collaborative test involving an unmanned aerial vehicle and an unmanned ground vehicle. The third issue this thesis addresses is that of soft sensor only data fusion. Soft-only fusion is a newer field than centralized or distributed hard sensor fusion. Because of the novelty of the field, the chapter on soft only fusion contains less background information and instead focuses on some new results in soft sensor data fusion. Specifically, it discusses a novel fuzzy logic based soft sensor data fusion method. This new method is tested using both simulations and field measurements. The biggest issue addressed in this thesis is that of combined hard and soft fusion. Fusion of hard and soft data is the newest area for research in the data fusion community; therefore, some of the largest theoretical contributions in this thesis are in the chapter on combined hard and soft fusion. This chapter presents a novel combined hard and soft data fusion method based on random set theory, which processes random set data using a particle filter. Furthermore, the particle filter is designed to be distributed across multiple robots and portable computers (used by human observers) so that there is no centralized failure point in the system. After laying out a theoretical groundwork for hard and soft sensor data fusion the thesis presents practical applications for hard and soft sensor data fusion in simulation. Through a series of three progressively more difficult simulations, some important hard and soft sensor data fusion capabilities are demonstrated. The first simulation demonstrates fusing data from a single soft sensor and a single hard sensor in

  17. Armature design for coaxial induction launchers

    SciTech Connect

    Andrews, J.A.; Devine, J.R. . Center for Electromechanics)

    1991-01-01

    This paper reports on the armature design for a coaxial induction launcher that is influenced by a large set of highly coupled parameters. The simplifying assumptions often employed in coaxial accelerator analysis, such as a uniform or sinusoidal axial distribution of the azimuthal armature current, are unrealistic in induction launchers with monolithic single-turn armatures. In order to better understand the true dynamic behavior of coaxial accelerators, the Center for Electromechanics at The University of Texas at Austin (CEM-UT) has developed series of computer codes based on the current filament method. By utilizing these performance codes in conjunction with electromagnetic (EM) and mechanical finite element programs, it is now possible to design high performance induction launchers with armatures that can withstand the considerable mechanical and thermal loads inherent in a coaxial accelerator launch.

  18. 1. MORRIS DAM TEST FACILITY (MDTF) AND VARIABLEANGLE LAUNCHER AS ...

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

    1. MORRIS DAM TEST FACILITY (MDTF) AND VARIABLE-ANGLE LAUNCHER AS SEEN FROM STATE HIGHWAY 39 NEAR MORRIS DAM LOOKING EAST. - Variable Angle Launcher Complex, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  19. Superconductive levitated armatures for electromagnetic launchers

    SciTech Connect

    Jasper, L.J.

    1988-03-14

    An electromagnetic railgun launcher and armature. The armature is made from superconducting material and is levitated between the rails of the launcher by the Meissner effect. The Meissner effect is created by cooling the armature and subjecting it to a magnetic field. The armature configuration has a closed-loop topology and defines two planes - one plane coincides with the plane of the rails; the other plane is oblique to the first. The armature configuration, when placed between the rails receives an unbalanced Lorentz force which accelerates the armature.

  20. 79. VIEW OF VAL FIRING RANGE LOOKING SOUTHWEST SHOWING LAUNCHER ...

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

    79. VIEW OF VAL FIRING RANGE LOOKING SOUTHWEST SHOWING LAUNCHER BRIDGE, BARGES, SONAR BUOY RANGE AND MORRIS DAM IN BACKGROUND, June 10, 1948. - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  1. Predicting bore deformations and launcher stresses in railguns

    SciTech Connect

    Davidson, R.F.; Cook, W.A.; Rabern, D.A.; Schnurr, N.M.

    1986-01-01

    The structural responses of launchers are important because they affect the projectile performance and the operating limits of the railgun system. Structural analysis makes it possible to make better decisions in launcher design. Example analyses of the Los Alamos HIMASS and Lethality Test System launchers are presented in this paper. Also, a discussion of the benefits and limitations of these analyses is included.

  2. Electromagnetic coilgun launcher for space applications

    NASA Astrophysics Data System (ADS)

    Turman, B. N.; Lipinski, R. J.

    1996-03-01

    A ground-based electrically-powered launcher could significantly reduce the complexity and cost of space launches for moderate-weight payloads. The electromagnetic launch complex could greatly reduce the amount of fuels handling, reduce the turn-around time between launches, allow more concurrence in launch preparation, reduce the manpower requirements for launch vehicle preparation and increase the reliability of launch by using more standardized vehicle preparations. The launch requires high acceleration, so the satellite package must be hardened. This paper presents results of a study to estimate the required launcher parameters, and estimate the cost of such a launch facility. This study is based on electromagnetic gun technology which is constrained to a coaxial geometry to take advantage of the efficiency of closely-coupled coils. The launcher energy and power requirements fall in the range of 40-260 GJ and 20-400 GW electric. Parametric evaluations have been conducted with a launcher length of 1-2 km, exit velocity of 1-6 km/s, and payloads to low earth orbit of 100-1000 kg.

  3. Dynamic Loads Affecting Artillery Launcher Crew

    DTIC Science & Technology

    2004-10-01

    limiters) front and rear wheel axles, the cabin, driving block, the launcher (or an open load-carrying body) as well as flexible- suppressing tyre ...Driver’s seat suspension change included the replacement of mechanical suspension with the pneumatic one, which can be characterized by a lower

  4. External wave-launcher study. Final report

    SciTech Connect

    Not Available

    1983-06-30

    The rationale for liquid dielectrically-loaded external wave-guide launchers is discussed. The arguments are strongly indicative that a liquid dielectric-filled waveguide system could be a practical technique for launching ICRH power into a fusion reactor. A detailed summary of the work performed in the study is presented.

  5. Electromagnetic coilgun launcher for space applications

    SciTech Connect

    Turman, B.N.; Lipinski, R.J.

    1996-03-01

    A ground-based electrically-powered launcher could significantly reduce the complexity and cost of space launches for moderate-weight payloads. The electromagnetic launch complex could greatly reduce the amount of fuels handling, reduce the turn-around time between launches, allow more concurrence in launch preparation, reduce the manpower requirements for launch vehicle preparation and increase the reliability of launch by using more standardized vehicle preparations. The launch requires high acceleration, so the satellite package must be hardened. This paper presents results of a study to estimate the required launcher parameters, and estimate the cost of such a launch facility. This study is based on electromagnetic gun technology which is constrained to a coaxial geometry to take advantage of the efficiency of closely-coupled coils. The launcher energy and power requirements fall in the range of 40{endash}260 GJ and 20{endash}400 GW electric. Parametric evaluations have been conducted with a launcher length of 1{endash}2 km, exit velocity of 1{endash}6 km/s, and payloads to low earth orbit of 100{endash}1000 kg. {copyright} {ital 1996 American Institute of Physics.}

  6. External wave launcher study. Final technical report

    SciTech Connect

    Moses, K.G.

    1986-06-26

    The overall purpose of this study is to explore the applicability of dielectric filled waveguide launchers to couple ion cyclotron resonant frequency (ICRF) power to magnetically confined plasma. The major advantage of dielectric filled launchers is that the geometrical dimensions of a waveguide launcher required to accommodate an electromagnetic wave of any given frequency can be reduced by the square root of the relative permittivity of the dielectric compared to air or vacuum waveguide dimensions. However, removal of the intense heat load deposited by 14 MeV neutrons in a solid dielectric filled waveguide heating system in close proximity to a fusion reactor presents several major problems: Heat is distributed throughout the volume of solid dielectric by energetic neutrons, which necessitates that a substantial fraction of the dielectric filled waveguide must be occupied by channels containing liquid coolant to remove the heat. The uniformity of the internal dielectric media of the waveguide is disrupted, and electromagnetic waves in the guide will be reflected and scattered at the discontinuities. It is highly questionable that a waveguide or waveguide launcher constructed in this manner will be an efficient means of transmitting ICRF power. This circumstance leads to employing liquid dielectrics which could satisfy both electromagnetic and coolant requirements of ICRF auxiliary launching systems simultaneously. Additionally, liquid dielectrics facilitate the motion of tuning structures through the media and preserve its dielectric uniformity in contrast to the tuning restrictions imposed by solid dielectrics in this regard.

  7. Electromagnetic coilgun launcher for space applications

    SciTech Connect

    Turman, B.N.; Lipinski, R.J.

    1995-10-01

    A ground-based electrically-powered launcher could significantly reduce the complexity and cost of space launches for moderate-weight payloads. The EM launch complex could greatly reduce the amount of fuels handling, reduce the turnaround time between launches, allow more concurrence in launch preparation, reduce the manpower requirements for launch vehicle preparation and increase the reliability of launch by using more standardized vehicle preparations. The launch requires high acceleration, so the satellite package must be hardened. This paper presents results of a study to estimate the required launcher parameters, and estimate the cost of such a launch facility. This study is based on electromagnetic gun technology which is constrained to a coaxial geometry to take advantage of the efficiency of closely-coupled coils. The launcher energy and power requirements fall in the range of 40 {minus} 260 GJ and 20 {minus} 400 GW electric. Parametric evaluations have been conducted with a launcher length of 1-2 km, exit velocity of 1-6 kn/s, and payloads to low earth orbit of 100 1000 kg.

  8. Ratio of effective temperature to pressure controls the mobility of sheared hard spheres.

    PubMed

    Haxton, Thomas K

    2012-01-01

    Using molecular dynamics simulations, we calculate fluctuations and responses for steadily sheared hard spheres over a wide range of packing fractions φ and shear strain rates γ[over ̇], using two different methods to dissipate energy. To a good approximation, shear stress and density fluctuations are related to their associated response functions by a single effective temperature T(eff) that is equal to or larger than the kinetic temperature T(kin). We find a crossover in the relationship between the relaxation time τ and the the nondimensionalized effective temperature T(eff)/pσ(3), where p is the pressure and σ is the sphere diameter. In the solid response regime, the behavior at a fixed packing fraction satisfies τ ̇γ∝exp(-cpσ(3)/T(eff)), where c depends weakly on φ, suggesting that the average local yield strain is controlled by the effective temperature in a way that is consistent with shear transformation zone theory. In the fluid response regime, the relaxation time depends on T(eff)/pσ(3) as it depends on T(kin)/pσ(3) in equilibrium. This regime includes both near-equilibrium conditions where T(eff)≃T(kin) and far-from-equilibrium conditions where T(eff)≠T(kin). We discuss the implications of our results for systems with soft repulsive interactions.

  9. A Cost Effective Automatic Balloon Launcher

    SciTech Connect

    Berrigan J. Michael

    2000-06-08

    Approximately 800,000 balloon-borne radiosondes are hand-launched each year, a cost and labor-intensive procedure. Development of a low-cost Automatic Radiosonde Launcher would allow the manual procedure to be replaced with a reliable and less expensive process. Balloon-borne radiosondes provide essential meteorological data used by forecasters and researchers around the globe. The National Weather service alone launches tens of thousands of sondes from sites across the US. Although worldwide launching of radiosondes has been done for many years, it remains a labor intensive and therefore expensive operation. Using its own funding and, more recently with the help of a Phase I SBIR grant, Visidyne, Inc. has begun investigating the feasibility of building an Automatic Radiosonde Launcher (ARL) that can be built at a cost that will be acceptable to the commercial marketplace. That work has led to the issuing of four patents covering important innovations that will allow us to meet that goal. Under the recent Phase I effort, solutions to many of the key problems have been tested in the laboratory and in real-world demonstrations in the field. The balloon filling, battery wetting, and launch release mechanisms were designed, built, and tested. A breadboard launcher was constructed and tested to prove feasibility of key system elements. Demonstration launches of radiosondes were performed using the breadboard launcher from the National Weather Service facility in Gray, ME, and from Hanscom AFB in Lexington, MA. The cost and size of a full scale shelter prevented us from building one during Phase I, however, we do have a design that will accomplish our goals. The Automatic Radiosonde Launcher will significantly reduce the cost of launching balloon-borne instruments. US and foreign weather services and atmospheric, climatological, and meteorological researchers will all benefit from this innovation.

  10. Future launchers strategy : the ariane 2010 initiative

    NASA Astrophysics Data System (ADS)

    Bonnal, Ch.; Eymard, M.; Soccodato, C.

    2001-03-01

    With the new cryogenic upper stage ESC, the European heavy launcher Ariane 5+ is perfectly suited to the space market envisioned for the coming decade: flexible to cope with any payload and commercially attractive despite a fierce competition. Current Arianespace projections for the following years 2010-2020 indicate two major trends: satellites may still become larger and may require very different final orbits; today's market largely dominated by GEO may well evolve, influenced by LEO operations such as those linked to ISS or by constellations, to remain competitive, the launch cost has to be reduced. The future generation of the European heavy launcher has therefore to focus on an ever increased flexibility with a drastic cost reduction. Two strategies are possible to achieve this double goal: reusable launchers, either partially or totally, may ease the access to space, limiting costly expendable stages; the assessment of their technical feasibility and financial viability is undergoing in Europe under the Future Launchers Technology Program (FLTP), expendable launchers, derived from the future Ariane 5+. This second way started by CNES at the end of year 1999 is called the "Ariane 2010 initiative". The main objectives are simultaneously an increase of 25% in performance and a reduction of 30% in launch cost wrt Ariane 5+. To achieve these very ambitious goals, numerous major modifications are studied: technical improvements : modifications of the Solid Rocket Boosters may consist in filament winding casing, increased loading, simplified casting, improved grain, simplified Thrust Vector Control, … evolution of the Vulcain engine leading to higher efficiency despite a simplified design, flow separation controlled nozzle extension, propellant management of the two cryogenic stages, simplified electrical system, increased standardization, for instance on flanged interfaces and manufacturing processes, operational improvements such as launch cycle simplification

  11. SIDON: A simulator of radio-frequency networks. Application to WEST ICRF launchers

    NASA Astrophysics Data System (ADS)

    Helou, Walid; Dumortier, Pierre; Durodié, Frédéric; Goniche, Marc; Hillairet, Julien; Mollard, Patrick; Berger-By, Gilles; Bernard, Jean-Michel; Colas, Laurent; Lombard, Gilles; Maggiora, Riccardo; Magne, Roland; Milanesio, Daniele; Moreau, Didier

    2015-12-01

    SIDON (SImulator of raDiO-frequency Networks) is an in-house developed Radio-Frequency (RF) network solver that has been implemented to cross-validate the design of WEST ICRF launchers and simulate their impedance matching algorithm while considering all mutual couplings and asymmetries. In this paper, the authors illustrate the theory of SIDON as well as results of its calculations. The authors have built time-varying plasma scenarios (a sequence of launchers front-faces L-mode and H-mode Z-matrices), where at each time step (1 millisecond here), SIDON solves the RF network. At the same time, when activated, the impedance matching algorithm controls the matching elements (vacuum capacitors) and thus their corresponding S-matrices. Typically a 1-second pulse requires around 10 seconds of computational time on a desktop computer. These tasks can be hardly handled by commercial RF software. This innovative work allows identifying strategies for the launchers future operation while insuring the limitations on the currents, voltages and electric fields, matching and Load-Resilience, as well as the required straps voltage amplitude/phase balance. In this paper, a particular attention is paid to the simulation of the launchers behavior when arcs appear at several locations of their circuits using SIDON calculator. This latter work shall confirm or identify strategies for the arc detection using various RF electrical signals. One shall note that the use of such solvers in not limited to ICRF launchers simulations but can be employed, in principle, to any linear or linearized RF problem.

  12. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-06-30

    Just north of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, technicians install the core stage forward skirt umbilical on the mobile launcher. The mobile launcher is designed to support the assembly, testing and check-out of the agency's Space Launch System (SLS) rocket and the Orion spacecraft.

  13. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-06-30

    Just north of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, a crane lifts the core stage forward skirt umbilical for installation onto the mobile launcher. The mobile launcher is designed to support the assembly, testing and check-out of the agency's Space Launch System (SLS) rocket and the Orion spacecraft.

  14. Three-phase hypervelocity projectile launcher

    DOEpatents

    Fugelso, L. Erik; Langner, Gerald C.; Burns, Kerry L.; Albright, James N.

    1994-01-01

    A hypervelocity projectile launcher for use in perforating borehole casings provides improved penetration into the surrounding rock structure. The launcher includes a first cylinder of explosive material that defines an axial air-filled cavity, a second cylinder of explosive material defining an axial frustum-shaped cavity abutting and axially aligned with the first cylinder. A pliant washer is located between and axially aligned with the first and second cylinders. The frustum shaped cavity is lined with a metal liner effective to form a projectile when the first and second cylinders are detonated. The washer forms a unique intermediate projectile in advance of the liner projectile and enables the liner projectile to further penetrate into and fracture the adjacent rock structure.

  15. Next Generation of Launcher & Space Vehicles Batteries

    NASA Astrophysics Data System (ADS)

    Laroye, J. F.; Brochard, P.; Grassien, J.-Y.; Masgrangeas, D.

    2008-09-01

    This paper presents several examples of Saft lithium batteries in use onboard launchers & space vehicles: ATV primary lithium manganese dioxide (LiMnO2) batteries and Rosetta primary lithium thionyl chloride (LiSOCl2) batteries as well as the VEGA rechargeable lithium-ion (Li-ion) avionics & thrust vector control (TVC) batteries.It gives an overview of possible chemistries and tradeoff to address these needs.

  16. Electromagnetic Launchers and Guns. Phase 1

    DTIC Science & Technology

    1980-06-01

    a high-speed maglev transportation system based on a linear synchronous motor (1,2,3). In 1975 Gerard K. O’Neill of Princeton University...fact that the very important railgun- homopolar launcher technology is already being pursued at Westinghouse and university of Texas, Austin. The...shown in Fig. 14 on the following page. There are three comparable options for energy storage: an engine-driven homopolar generator followed by an

  17. Characterization of the Electrostatic Environment of Launchers

    NASA Astrophysics Data System (ADS)

    Soyah, Jamila; Mantion, Pascal; Herlem, Yannick

    2016-05-01

    The purpose of this study was to update knowledge in characterization of the electrostatic environment of launchers in order to be able to propose reductions of design constraints.The first part of this study showed that flashover discharges are the most energetic discharges likely to occur on a launcher. They are mostly due to accumulations of charges by triboelectricity on the external surface of the launcher while flying through clouds containing a lot of small solid particles.Actually flashover discharges are mitigated by limiting the surface's resistance of dielectric materials such as thermal protection set on the external skin of the launcher, thanks to antistatic paints that avoid significant accumulations of charges.But this specified limitation leads to a lot of non- conformances during production phases and, as a result, this leads to additional costs and delays in launches campaigns. That is why on-ground tests have been defined in order to assess the accessibility of a relaxation of those specifications, which would reduce non-conformances.On-ground tests have been carried out, in the second part, on samples of thermal protections covered with antistatic paints with different degraded values of surface resistance. These tests aimed at checking in which conditions a surface discharge can occur in order to deduce a relationship between characteristics of the samples (surface resistance, half-discharge time) and the occurrence of a surface discharge, at ambient pressure and at low pressure.In the third part, in-flight experiments have been defined in order to confirm some hypotheses considered in the study and to assess some parameters in a more accurate way like the incoming charges density per surface unit or the voltage between stages when they get separated, in order to assess more accurately whether the unwinding equalization wire dedicated to maintain the electrostatic balance between stages is necessary or not.

  18. Impact performance of large scale electromagnetic launchers

    SciTech Connect

    Fahrenthold, E.P. . Dept. of Mechanical Engineering)

    1991-01-01

    This paper reports on the development of high performance electromagnetic launchers and associated pulsed power supplies which has led to the aerodynamic and structural design of new projectile types. The impact performance of monolithic railgun projectiles between one and four kilograms in mass has been estimated using Lagrangian hydrocode simulations at velocities up to three kilometers per second. The simulation predictions are within expected bounds, based on existing correlations of experimental measurements on cylindrical projectiles of equivalent mass.

  19. Launchers - The first 50-year cycle

    NASA Astrophysics Data System (ADS)

    Pardoe, G. K. C.

    1986-11-01

    An assessment is made of the development history of spacecraft launch vehicles to the present date, with attention to mission economics and the criteria of profitability. Three technological generations are postulated: that dominated by expendable launch vehicles, lasting from 1957 to the introduction of the Space Shuttle; the Space Shuttle period of semireusable launch vehicles; and the soon-to-be-inaugurated era of fully reusable launchers which are expected to begin operations around the year 2000.

  20. Final Report Advanced Quasioptical Launcher System

    SciTech Connect

    Jeffrey Neilson

    2010-04-30

    This program developed an analytical design tool for designing antenna and mirror systems to convert whispering gallery RF modes to Gaussian or HE11 modes. Whispering gallery modes are generated by gyrotrons used for electron cyclotron heating of fusion plasmas in tokamaks. These modes cannot be easily transmitted and must be converted to free space or waveguide modes compatible with transmission line systems.This program improved the capability of SURF3D/LOT, which was initially developed in a previous SBIR program. This suite of codes revolutionized quasi-optical launcher design, and this code, or equivalent codes, are now used worldwide. This program added functionality to SURF3D/LOT to allow creating of more compact launcher and mirror systems and provide direct coupling to corrugated waveguide within the vacuum envelope of the gyrotron. Analysis was also extended to include full-wave analysis of mirror transmission line systems. The code includes a graphical user interface and is available for advanced design of launcher systems.

  1. Additive Layer Manufacturing for Launcher's Applications

    NASA Astrophysics Data System (ADS)

    Vilanova, J.; Romera, P.; Lasagni, F.; Zorrilla, A.; Perinan, A.

    2014-06-01

    In the next years the European space industry has the challenge of maintaining its competitiveness in launch vehicles (LV) production, due to the growth of competition worldwide. It has to assure its position developing new applied technologies. In this field the effort is focussed on the production of short series of customized products, like payloads, flight components or launcher parts. ALM (Additive Layer Manufacturing) could be a powerful tool that offers new competitiveness factors for this industry, comprising a set of emerging technologies that are becoming a competitor to forming, casting and machining as well as being utilised directly as a complementary alternative.Originally used for prototypes and models, now ALM becomes a very useful technology capable to fabricate functional parts for the space industrial sector. Its demands on rapid technologies are different to "earth" industries, and they aren't so easily satisfied because space is a field with different requirements depending on its application: launchers, reusable vehicles, satellites, probes, low gravity researches, manned spacecraft, or even moon and planetary exploration.This paper reports on the ALM potential applications, under ESA requirements, exploring the challenges and possibilities for its use in the launchers market, trying to answer two basic questions: the first one, whether ALM is a mature technology to be ready for its use as flight hardware; and the second one, if it can be used to reduce the product cycle, and consequently, the development, production and operational costs.

  2. Nondestructive inspection of a composite missile launcher

    NASA Astrophysics Data System (ADS)

    Ley, O.; Chung, S.; Butera, M.; Valatka, T.; Triplett, M. H.; Godinez, V.

    2012-05-01

    Lighter weight alternatives are being sought to replace metallic components currently used in high performance aviation and missile systems. Benefits of lightweight, high strength carbon fiber reinforced composites in missile launchers and rocket motor cases include improved fuel economy, increased flight times, enhanced lethality and/or increased velocity. In this work, various nondestructive inspection techniques are investigated for the damage assessment of a composite missile launcher system for use in U.S. Army attack helicopters. The launcher system, which includes rails and a hardback, can be subject to impact damage from accidental tool drops, routine operation, and/or ballistic threats. The composite hardback and the launch rails both have complex geometries that can challenge the inspection process. Scanning techniques such as line scanning thermography, ultrasonic, and acousto-ultrasonics will be used and compared to determine damage detection accuracy, reliability, and efficiency. Results will also be compared with visual observations to determine if there is a correlation. The goal is to establish an inspection method that quickly and accurately assesses damage extent in order to minimize service time and return the missile system back into the field [1].

  3. Design and development of mode launcher for high frequency Gyrotron

    NASA Astrophysics Data System (ADS)

    Alaria, Mukesh Kumar; Sinha, A. K.; Khatun, H.

    2016-03-01

    In this paper, we describe the design and development of helical cut smooth wall mode launcher for high frequency and high power Gyrotron. A Vlasov-type helical cut mode launcher for converting TE22,6 mode to a Gaussian mode has been designed for 120 GHz, 1 MW Gyrotron. The initial design of mode launcher has been optimized using LOT/SURF-3D software. The mode launcher diameter and length are optimized considering the minimum return loss and the minimum insertion loss by using CST microwave studio. The return loss (S11) and insertion loss (S21) performance of helical cut smooth wall mode launcher have been obtained using CST-Microwave Studio. The fabrication of Vlasov-type helical cut mode launcher for 120 GHz Gyrotron has also been carried out.

  4. Photographic copy of photograph, view of rail launcher used for ...

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

    Photographic copy of photograph, view of rail launcher used for 'Baby Corporal E' missiles on 6 and 7 May 1946 at JPL-Muroc Army Air Base (later Edwards Air Force Base) (This launcher was also used for 'Baby WAC' missiles at Goldstone, Fort Irwin, California in 1945). Photocopy of 35mm photograph made in December 1994, looking west with Test Stand 'A' immediately behind the rail launcher. - Jet Propulsion Laboratory Edwards Facility, Edwards Air Force Base, Boron, Kern County, CA

  5. Multirail electromagnetic launcher powered from a pulsed magnetohydrodynamic generator

    NASA Astrophysics Data System (ADS)

    Afonin, A. G.; Butov, V. G.; Panchenko, V. P.; Sinyaev, S. V.; Solonenko, V. A.; Shvetsov, G. A.; Yakushev, A. A.

    2015-09-01

    The operation of an electromagnetic multirail launcher of solids powered from a pulsed magnetohydrodynamic (MHD) generator is studied. The plasma flow in the channel of the pulsed MHD generator and the possibility of launching solids in a rapid-fire mode of launcher operation are considered. It is shown that this mode of launcher operation can be implemented by matching the plasma flow dynamics in the channel of the pulsed MHD generator and the launching conditions. It is also shown that powerful pulsed MHD generators can be used as a source of electrical energy for rapid-fire electromagnetic rail launchers operating in a burst mode.

  6. 94. 22'X34' original blueprint, VariableAngle Launcher, 'MAIN RAIL' drawn at ...

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

    94. 22'X34' original blueprint, Variable-Angle Launcher, 'MAIN RAIL' drawn at 1'=1'-0'. (BUORD Sketch # 207406). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  7. An efficient method for preliminary launcher/satellite coupled loads analysis by satellite developers using launcher user's manual data

    NASA Astrophysics Data System (ADS)

    Stavrinidis, Constantinos; Fransen, Sebastiaan

    2016-03-01

    This paper presents a method used over the years by the authors in performing preliminary launcher/satellite coupled loads analysis (CLA) using in an innovative manner the quasi-static design loads defined in the launcher user's manual (LUM). The rationale and the value of the approach are addressed first. Subsequently the use of the method is presented, and the results derived by satellite developers using the proposed preliminary launcher/satellite CLA are compared with preliminary or full CLA results performed by launcher authorities for a number of industrial satellite applications.

  8. Application of melt-textured YBCO to electromagnetic launchers

    NASA Astrophysics Data System (ADS)

    Putman, P. T.; Zhou, Y. X.; Fang, H.; Klawitter, A.; Salama, K.

    2005-02-01

    Melt-textured YBCO superconductors are capable of carrying higher current densities than comparable copper conductors, and can therefore be used in electromechanical devices requiring high power densities. The advantage of textured YBCO superconductors is most pronounced in large systems such as electromagnetic launchers for aircraft carriers. In general, an electromagnetic launcher consists of a series of stationary pulsed electromagnets (the primary), which attract and/or repel a carriage carrying one or more magnets (the secondary). Several possibilities exist for the incorporation of HTSs into EM launchers, with the most direct being upgrading the magnets in the secondary to melt-textured YBCO. A system was developed to study propulsive force in a coaxial-type launcher. Results from this study are presented and their implications for launcher development discussed. A second type of launcher was also studied, with a power supply integrated into the launcher primary, so that the primary serves as a superconducting magnetic energy storage system. A method of optimizing energy conversion in a system of this type has been found. The time dependence of the magnetic field in this type of launcher is presented.

  9. 23. VIEW DOWN INTO LAUNCHER AND FLAME BUCKET FROM STATION ...

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

    23. VIEW DOWN INTO LAUNCHER AND FLAME BUCKET FROM STATION 48 IN SLC-3W MST. NOTE REMOVABLE METAL PLANKS BELOW LAUNCHER AND ROPE NET OVER FLAME BUCKET. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 West, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  10. 1. VARIABLEANGLE LAUNCHER CAMERA CAR, VIEW OF CAMERA CAR AND ...

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

    1. VARIABLE-ANGLE LAUNCHER CAMERA CAR, VIEW OF CAMERA CAR AND TRACK WITH CAMERA STATION ABOVE LOOKING NORTH TAKEN FROM RESERVOIR. - Variable Angle Launcher Complex, Camera Car & Track, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  11. 7. VARIABLEANGLE LAUNCHER DEDICATION PLAQUE SHOWING JAMES H. JENNISON (LEFT), ...

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

    7. VARIABLE-ANGLE LAUNCHER DEDICATION PLAQUE SHOWING JAMES H. JENNISON (LEFT), AND W.H. SAYLOR (RIGHT), AT THE DEDICATION CEREMONY, May 7, 1948. (Original photograph in possession of Dave Willis, San Diego, California.) - Variable Angle Launcher Complex, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  12. A hypervelocity projectile launcher for well perforation

    SciTech Connect

    Albright, J.N.; Fugelso, L.E.; Lagner, G.C.; Burns, K.L.

    1989-01-01

    Current oil well perforation techniques use low- to medium-velocity gun launchers for completing wells in soft rock. Shaped-charge jets are normally used in harder, more competent rock. A device to create a much higher velocity projectile was designed. This launcher will provide an alternative technique to be used when the conventional devices do not yield the maximum well performance. It is an adaptation of the axial cavity in a high explosive (HE) annulus design, with the axial cavity being filled with a low density foam material. Two configurations were tested; both had an HE annulus filled with organic foam, one had a projectile. Comparison of the two shots was made. A time sequence of Image Intensifier Camera photographs and sequential, orthogonal flash x-ray radiographs provided information on the propagation of the foam fragments, the first shock wave disturbance, the projectile motion and deformation, and the direct shock wave transmission from the main HE charge. DYNA2D calculations were made to assist in the experimental interpretation. 25 refs., 9 figs.

  13. A future European launcher - Ariane 5/Hermes

    NASA Astrophysics Data System (ADS)

    Cretenet, J. C.; Marx, P.

    1984-12-01

    The development of the Ariane launch vehicle was begun in Europe ten years ago to provide independence in terms of the commercial exploitation of telecommunications satellites. In connection with the spectacular development of the satellite market and, consequently, the launch services market, Ariane has now also a commercial objective, which is related to the penetration of the international launch services market. The current capacity of Ariane is adequate for short and medium-term European launch requirements. However, in the longer term, Ariane's capacity is insufficient and a new launcher is needed. It is attempted to evaluate future launching requirements for the 1995-2000 period, taking into account competing launch resources related to the U.S. Space Shuttle. The results of this evaluation lead to a discussion of the characteristics of the Ariane 5, which is to be the new launcher for the 1990s. Attention is given to improved geostationary orbit service, low orbit injection, and the Hermes European manned system.

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

    NASA Astrophysics Data System (ADS)

    Fatemi, Javad; van der Bas, Finn

    2014-06-01

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

  15. Explosively driven hypervelocity launcher: Second-stage augmentation techniques

    NASA Technical Reports Server (NTRS)

    Baum, D. W.

    1973-01-01

    The results are described of a continuing study aimed at developing a two-stage explosively driven hypervelocity launcher capable of achieving projectile velocities between 15 and 20 km/sec. The testing and evaluation of a new cylindrical impact technique for collapsing the barrel of two-stage launcher are reported. Previous two-stage launchers have been limited in ultimate performance by incomplete barrel collapse behind the projectile. The cylindrical impact technique explosively collapses a steel tube concentric with and surrounding the barrel of the launcher. The impact of the tube on the barrel produces extremely high stresses which cause the barrel to collapse. The collapse rate can be adjusted by appropriate variation of the explosive charge and tubing parameters. Launcher experiments demonstrated that the technique did achieve complete barrel collapse and form a second-stage piston. However, jetting occurred in the barrel collapse process and was responsible for severe projectile damage.

  16. KENNEDY SPACE CENTER, FLA. - Like candles embedded in a sculptured “cake,” the Mobile Launcher Platform (MLP) number 3 with twin solid rocket boosters bolted to it inches along the crawlerway at various speeds up to 1 mph in an effort to achieve vibration data gathering goals. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Like candles embedded in a sculptured “cake,” the Mobile Launcher Platform (MLP) number 3 with twin solid rocket boosters bolted to it inches along the crawlerway at various speeds up to 1 mph in an effort to achieve vibration data gathering goals. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  17. KENNEDY SPACE CENTER, FLA. - The Space Shuttle Discovery on its Mobile Launcher Platform makes its slow 3.4-mile trek from the Vehicle Assembly Building to Launch Pad 39A in preparation for the STS-82 mission. In the foreground is the U.S. flag at the Press Site area. A seven-member crew will perform the second servicing of the orbiting Hubble Space Telescope (HST) during the 10-day STS-82 mission, which is targeted for a Feb. 11 liftoff.

    NASA Image and Video Library

    1997-01-17

    KENNEDY SPACE CENTER, FLA. - The Space Shuttle Discovery on its Mobile Launcher Platform makes its slow 3.4-mile trek from the Vehicle Assembly Building to Launch Pad 39A in preparation for the STS-82 mission. In the foreground is the U.S. flag at the Press Site area. A seven-member crew will perform the second servicing of the orbiting Hubble Space Telescope (HST) during the 10-day STS-82 mission, which is targeted for a Feb. 11 liftoff.

  18. KENNEDY SPACE CENTER, FLA. - The rising sun and some scattered clouds provide a picturesque backdrop for the Space Shuttle Discovery as it travels along the crawlerway toward Launch Pad 39A in preparation for the STS-82 mission. The Shuttle is on a Mobile Launcher Platform, and the entire assemblage is being carried by a large, tracked vehicle called the crawler transporter. A seven-member crew will perform the second servicing of the orbiting Hubble Space Telescope (HST) during the 10-day STS-82 flight, whcih is targeted for a Feb. 11 liftoff.

    NASA Image and Video Library

    1997-01-17

    KENNEDY SPACE CENTER, FLA. - The rising sun and some scattered clouds provide a picturesque backdrop for the Space Shuttle Discovery as it travels along the crawlerway toward Launch Pad 39A in preparation for the STS-82 mission. The Shuttle is on a Mobile Launcher Platform, and the entire assemblage is being carried by a large, tracked vehicle called the crawler transporter. A seven-member crew will perform the second servicing of the orbiting Hubble Space Telescope (HST) during the 10-day STS-82 flight, whcih is targeted for a Feb. 11 liftoff.

  19. Modeling the effects of surfactant, hardness, and natural organic matter on deposition and mobility of silver nanoparticles in saturated porous media.

    PubMed

    Park, Chang Min; Heo, Jiyong; Her, Namguk; Chu, Kyoung Hoon; Jang, Min; Yoon, Yeomin

    2016-10-15

    This study aims to provide insights into the mechanisms governing the deposition and retention of silver nanoparticles (AgNPs) in saturated porous media. Column experiments were conducted with quartz sand under saturated conditions to investigate the deposition kinetics of AgNPs, their mobility at different groundwater hardnesses (10-400 mg/L as CaCO3), and humic acid (HA, 0-50 mg/L as dissolved organic carbon [DOC]). An anionic surfactant, sodium dodecyl sulfate (SDS), was used as a dispersing agent to prepare a SDS-AgNPs suspension. The deposition kinetics of AgNPs were highly sensitive to the surfactant concentration, ionic strength, and cation type in solution. The breakthrough curves (BTCs) of SDS-AgNPs suggested that the transport and retention were influenced by groundwater hardness and HA. At low water hardness and high HA, high mobility of SDS-AgNPs was observed in saturated conditions. However, the retention of SDS-AgNPs increased substantially in very hard water with a low concentration of HA, because of a decreased primary energy barrier and the straining effect during the course of transport experiments. A modified clean-bed filtration theory and a two-site kinetic attachment model showed good fits with the BTCs of SDS-AgNPs. The fitted model parameters (katt and kstr) could be used successfully to describe that the retention behaviors were dominated by electrostatic and electrosteric repulsion, based on extended Derjaguin-Landau-Vaerwey-Overbeek calculations. Copyright © 2016 Elsevier Ltd. All rights reserved.

  20. ICRF Traveling Wave launcher for fusion devices

    NASA Astrophysics Data System (ADS)

    Ragona, R.

    2017-05-01

    Ion Cyclotron Resonance Heating and Current Drive is a method that has the ability to heat directly the ions in the Deuterium-Tritrium fuel to the high temperature needed for the fusion reaction to works. The capability of efficiently couple the Radio Frequency power to the plasma plays a big role in the overall performance of a fusion device. A Traveling Wave Antenna in a resonant ring configuration is a good candidate for an Ion Cyclotron Resonance Heating and Current Drive system. It has the capability to increase the coupled power with respect to present designs and to have a highly selective power spectrum that can be peaked around the maximally absorbed wave. It is also insensitive to the loading variations due to fluctuation of the plasma edge increasing the reliability and the efficiency of the system. It works as a low power density launcher due to the possible large number of current carrying elements.

  1. Thermal analysis of electromagnetic launcher rails

    SciTech Connect

    Schnurr, N.M.

    1987-10-01

    A numerical technique has been developed to analyze the combined thermal and electric field diffusion in electromagnetic launcher rails. TOPAZ2D, a two-dimensional finite-element thermal analysis code, has been adapted for this purpose. The resulting code, TOPAZRG, was used to predict the temperature field in the rails of the Lethality Test System being constructed at Los Alamos. Results of those calculations indicate the possibility of localized melting at the rail corners under full-power conditions. A parametric study was made to determine the effect of using tungsten coatings to prevent the melting of rail surfaces. The results of those computations show that the time to melt for a given surface heat flux can be increased by a factor of 2.8. Optimum coating thicknesses were determined for a range of heat fluxes. 11 refs.

  2. Infrared tracker for a portable missile launcher

    SciTech Connect

    Carlson, J.J.

    1993-07-13

    An infrared beam tracker is described for arrangement to a housing that is unitary with a portable missile launcher, comprising: a rotating beam splitter positioned to intercept the infrared beam passing a first portion of the beam through the beam splitter along a first direction and reflecting the remaining portion along a different direction; a first infrared detector for receiving the beam reflected portion from the beam splitter and produce electric signals responsive thereto; a second infrared detector for receiving the beam portion that passes through the beam splitter and providing electric signals responsive thereto; and means interconnected to the first and second infrared detectors and responsive to the electric signals generated by said detectors for determining errors in missile flight direction and communicating course correction information to the missile.

  3. Non-Rocket Missile Rope Launcher

    NASA Technical Reports Server (NTRS)

    Bolonkin, Alexander

    2002-01-01

    The method, installation, and estimation for delivering payload and missiles into outer space are presented. This method uses, in general, the engines and straight or closed-loop cables disposed on a planet surface. The installation consists of a space apparatus, power drive stations located along trajectory of the apparatus, the cables connected to the apparatus and to the power stations, a system for suspending the cable, and disconnected device. The drive stations accelerate the apparatus up to hypersonic speed. The estimations and computations show the possibility of making these projects a reality in a short period of time (see attached project: launcher for missiles and loads). The launch will be very cheap $1-$2 per LB. We need only light strong cable, which can be made from artificial fibers, whiskers, nanotubes, which exist in industry and scientific laboratories.

  4. Shuttle Hitchhiker Experiment Launcher System (SHELS)

    NASA Technical Reports Server (NTRS)

    Daelemans, Gerry

    1999-01-01

    NASA's Goddard Space Flight Center Shuttle Small Payloads Project (SSPP), in partnership with the United States Air Force and NASA's Explorer Program, is developing a Shuttle based launch system called SHELS (Shuttle Hitchhiker Experiment Launcher System), which shall be capable of launching up to a 400 pound spacecraft from the Shuttle cargo bay. SHELS consists of a Marman band clamp push-plate ejection system mounted to a launch structure; the launch structure is mounted to one Orbiter sidewall adapter beam. Avionics mounted to the adapter beam will interface with Orbiter electrical services and provide optional umbilical services and ejection circuitry. SHELS provides an array of manifesting possibilities to a wide range of satellites.

  5. Non-US electrodynamic launchers research and development

    SciTech Connect

    Parker, J.V.; Batteh, J.H.; Greig, J.R.; Keefer, D.; McNab, I.R.; Zabar, Z.

    1994-11-01

    Electrodynamic launcher research and development work of scientists outside the United States is analyzed and assessed by six internationally recognized US experts in the field of electromagnetic and electrothermal launchers. The assessment covers five broad technology areas: (1) Experimental railguns; (2) Railgun theory and design; (3) Induction launchers; (4) Electrothermal guns; (5) Energy storage and power supplies. The overall conclusion is that non-US work on electrodynamic launchers is maturing rapidly after a relatively late start in many countries. No foreign program challenges the US efforts in scope, but it is evident that the United States may be surpassed in some technologies within the next few years. Until recently, published Russian work focused on hypervelocity for research purposes. Within the last two years, large facilities have been described where military-oriented development has been underway since the mid-1980s. Financial support for these large facilities appears to have collapsed, leaving no effective effort to develop practical launchers for military or civilian applications. Electrodynamic launcher research in Europe is making rapid progress by focusing on a single application, tactical launchers for the military. Four major laboratories, in Britain, France, Germany, and the Netherlands, are working on this problem. Though narrower in scope than the US effort, the European work enjoys a continuity of support that has accelerated its progress. The next decade will see the deployment of electrodynamic launcher technology, probably in the form of an electrothermal-chemical upgrade for an existing gun system. The time scale for deployment of electromagnetic launchers is entirely dependent on the level of research-and-development effort. If resources remain limited, the advantage will lie with cooperative efforts that have reasonably stable funding such as the present French-German program.

  6. The Ariane 5 Launcher - Mid-way to success

    NASA Astrophysics Data System (ADS)

    Durand, J. H.; van Gaver, A.

    1992-08-01

    The paper discusses the salient features of the ESA's Ariane 5 Launcher concept, which retains the dual launch capability of the Ariane-sequence launchers but will be more economical and more reliable than Ariane 4 and will be able to accommodate the needs of the Columbus mission to launch the PPF polar platform and the free-flying laboratory. Attention is given to the objectives, performance, and schedule of Ariane 5; the launcher configuration; the flight guidance and vehicle control; the mission profile; and the ground infrastructure. The launcher configuration of Ariane 5 is made of two parts: a lower complex which is identical to all missions (and is comprised of the cryotechnic Vulcain engine, a tank housing LH2 and LO2, the fluid feed and pressurization systems, the electrical and pyrotechnical equipment, and a forward skirt which transmits thrust of main-stage and solid boosters to the upper complex), and an upper complex, which is specific for each case.

  7. 56. VIEW OF LAUNCHER FROM SOUTHWEST. NITROGEN CONTROL UNIT ON ...

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

    56. VIEW OF LAUNCHER FROM SOUTHWEST. NITROGEN CONTROL UNIT ON RIGHT; UMBILICAL MAST ON LEFT. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  8. The XLLGG — A Hypervelocity Launcher for Impact Cratering Research

    NASA Astrophysics Data System (ADS)

    Lexow, B.; Bückle, A.; Wickert, M.; Hiermaier, S.

    2015-09-01

    Hypervelocity launchers are used to accelerate projectiles that simulate impacting meteoroids or asteroids. The XLLGG (eXtra Large Light Gas Gun) at the EMI (Ernst-Mach-Institute) was used within the MEMIN program.

  9. LH Power Losses In Front of the JET Launcher

    SciTech Connect

    Jacquet, P.; Arnoux, G.; Kirov, K.; Mailloux, J.; Mayoral, M.-L.; Ongena, J.

    2009-11-26

    In recent JET experiments, Lower Hybrid (LH) power losses in the Scrape-Off Layer (SOL) were characterized using infra-red (IR) thermography. Hot spots were observed on objects intercepting the field lines passing in front of the LH launcher, i.e. on poloidal limiters and on dumplates located at the top of the tokamak; their locations being in good agreement with magnetic field line tracing using the EFIT equilibrium code. The dumplate temperature was monitored while scanning the launcher position so that the radial distance between field lines intercepting the hot spots and the launcher was increased up to 3.5 cm. The dissipation layer in front of the launcher was estimated to be at least 3.5 cm wide, in agreement with recent measurements on Tore-Supra, but not with simple models that predict a dissipation layer in the mm range.

  10. LH Power Losses In Front of the JET Launcher

    NASA Astrophysics Data System (ADS)

    Jacquet, P.; Arnoux, G.; Colas, L.; Delpech, L.; Ekedahl, A.; Frigione, D.; Goniche, M.; Kirov, K.; Leguen, F.; Mailloux, J.; Mayoral, M.-L.; Ongena, J.; Petrzilka, V.; Portafaix, C.; Rimini, F.

    2009-11-01

    In recent JET experiments, Lower Hybrid (LH) power losses in the Scrape-Off Layer (SOL) were characterized using infra-red (IR) thermography. Hot spots were observed on objects intercepting the field lines passing in front of the LH launcher, i.e. on poloidal limiters and on dumplates located at the top of the tokamak; their locations being in good agreement with magnetic field line tracing using the EFIT equilibrium code. The dumplate temperature was monitored while scanning the launcher position so that the radial distance between field lines intercepting the hot spots and the launcher was increased up to 3.5 cm. The dissipation layer in front of the launcher was estimated to be at least 3.5 cm wide, in agreement with recent measurements on Tore-Supra, but not with simple models that predict a dissipation layer in the mm range.

  11. Use of mobile phones for improving vaccination coverage among children living in rural hard-to-reach areas and urban streets of Bangladesh

    PubMed Central

    Uddin, Md. Jasim; Shamsuzzaman, Md.; Horng, Lily; Labrique, Alain; Vasudevan, Lavanya; Zeller, Kelsey; Chowdhury, Mridul; Larson, Charles P.; Bishai, David; Alam, Nurul

    2016-01-01

    In Bangladesh, full vaccination rates among children living in rural hard-to-reach areas and urban streets are low. We conducted a quasi-experimental pre-post study of a 12-month mobile phone intervention to improve vaccination among 0–11 months old children in rural hard-to-reach and urban street dweller areas. Software named “mTika” was employed within the existing public health system to electronically register each child’s birth and remind mothers about upcoming vaccination dates with text messages. Android smart phones with mTika were provided to all health assistants/vaccinators and supervisors in intervention areas, while mothers used plain cell phones already owned by themselves or their families. Pre and post-intervention vaccination coverage was surveyed in intervention and control areas. Among children over 298 days old, full vaccination coverage actually decreased in control areas – rural baseline 65.9% to endline 55.2% and urban baseline 44.5% to endline 33.9% – while increasing in intervention areas from rural baseline 58.9% to endline 76*8%, difference +18.8% (95% CI 5.7–31.9) and urban baseline 40.7% to endline 57.1%, difference +16.5% (95% CI 3.9–29.0). Difference-in-difference (DID) estimates were +29.5% for rural intervention versus control areas and +27.1% for urban areas for full vaccination in children over 298 days old, and logistic regression adjusting for maternal education, mobile phone ownership, and sex of child showed intervention effect odds ratio (OR) of 3.8 (95% CI 1.5–9.2) in rural areas and 3.0 (95% CI 1.4–6.4) in urban areas. Among all age groups, intervention effects on age-appropriate vaccination coverage were positive: DIDs +13.1–30.5% and ORs 2.5–4.6 (p < 0.001 in all comparisons). Qualitative data showed the intervention was well-accepted. Our study demonstrated that a mobile phone intervention can improve vaccination coverage in rural hard-to-reach and urban street dweller communities in Bangladesh

  12. Use of mobile phones for improving vaccination coverage among children living in rural hard-to-reach areas and urban streets of Bangladesh.

    PubMed

    Uddin, Md Jasim; Shamsuzzaman, Md; Horng, Lily; Labrique, Alain; Vasudevan, Lavanya; Zeller, Kelsey; Chowdhury, Mridul; Larson, Charles P; Bishai, David; Alam, Nurul

    2016-01-04

    In Bangladesh, full vaccination rates among children living in rural hard-to-reach areas and urban streets are low. We conducted a quasi-experimental pre-post study of a 12-month mobile phone intervention to improve vaccination among 0-11 months old children in rural hard-to-reach and urban street dweller areas. Software named "mTika" was employed within the existing public health system to electronically register each child's birth and remind mothers about upcoming vaccination dates with text messages. Android smart phones with mTika were provided to all health assistants/vaccinators and supervisors in intervention areas, while mothers used plain cell phones already owned by themselves or their families. Pre and post-intervention vaccination coverage was surveyed in intervention and control areas. Among children over 298 days old, full vaccination coverage actually decreased in control areas--rural baseline 65.9% to endline 55.2% and urban baseline 44.5% to endline 33.9%--while increasing in intervention areas from rural baseline 58.9% to endline 76*8%, difference +18.8% (95% CI 5.7-31.9) and urban baseline 40.7% to endline 57.1%, difference +16.5% (95% CI 3.9-29.0). Difference-in-difference (DID) estimates were +29.5% for rural intervention versus control areas and +27.1% for urban areas for full vaccination in children over 298 days old, and logistic regression adjusting for maternal education, mobile phone ownership, and sex of child showed intervention effect odds ratio (OR) of 3.8 (95% CI 1.5-9.2) in rural areas and 3.0 (95% CI 1.4-6.4) in urban areas. Among all age groups, intervention effects on age-appropriate vaccination coverage were positive: DIDs +13.1-30.5% and ORs 2.5-4.6 (p<0.001 in all comparisons). Qualitative data showed the intervention was well-accepted. Our study demonstrated that a mobile phone intervention can improve vaccination coverage in rural hard-to-reach and urban street dweller communities in Bangladesh. This small-scale successful

  13. Pellet acceleration using an ablation-controlled electrothermal launcher

    SciTech Connect

    Kincaid, R.W.; Bourham, M.A.; Gilligan, J.G.

    1995-12-31

    The NCSU ablation-controlled electrothermal launcher SIRENS has been used to accelerate plastic (Lexan polycarbonate) pellets to investigate the possibility of using electrothermal launchers as frozen pellet injectors for tokamak fueling. Successful installation of such a device would include a protective shell (sabot) to shield the hydrogenic pellet from ablation and allow it to maintain its integrity throughout the acceleration. The SIRENS device has been modified to include specially designed barrel sections equipped with diagnostic ports.

  14. Computational model for simulation small testing launcher, technical solution

    NASA Astrophysics Data System (ADS)

    Chelaru, Teodor-Viorel; Cristian, Barbu; Chelaru, Adrian

    2014-12-01

    The purpose of this paper is to present some aspects regarding the computational model and technical solutions for multistage suborbital launcher for testing (SLT) used to test spatial equipment and scientific measurements. The computational model consists in numerical simulation of SLT evolution for different start conditions. The launcher model presented will be with six degrees of freedom (6DOF) and variable mass. The results analysed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize a small multi-stage launcher, by recycling military rocket motors. From technical point of view, the paper is focused on national project "Suborbital Launcher for Testing" (SLT), which is based on hybrid propulsion and control systems, obtained through an original design. Therefore, while classical suborbital sounding rockets are unguided and they use as propulsion solid fuel motor having an uncontrolled ballistic flight, SLT project is introducing a different approach, by proposing the creation of a guided suborbital launcher, which is basically a satellite launcher at a smaller scale, containing its main subsystems. This is why the project itself can be considered an intermediary step in the development of a wider range of launching systems based on hybrid propulsion technology, which may have a major impact in the future European launchers programs. SLT project, as it is shown in the title, has two major objectives: first, a short term objective, which consists in obtaining a suborbital launching system which will be able to go into service in a predictable period of time, and a long term objective that consists in the development and testing of some unconventional sub-systems which will be integrated later in the satellite launcher as a part of the European space program. This is why the technical content of the project must be carried out beyond the range of the existing suborbital vehicle

  15. Para: a computer simulation code for plasma driven electromagnetic launchers

    SciTech Connect

    Thio, Y.-C.

    1983-03-01

    A computer code for simulation of rail-type accelerators utilizing a plasma armature has been developed and is described in detail. Some time varying properties of the plasma are taken into account in this code thus allowing the development of a dynamical model of the behavior of a plasma in a rail-type electromagnetic launcher. The code is being successfully used to predict and analyse experiments on small calibre rail-gun launchers.

  16. Design of pressure vessel cascades for electromagnetic launchers

    SciTech Connect

    Fahrenthold, E.P. )

    1989-08-01

    The relatively recent development of very high-energy density pulsed power supplies has motivated a renewed interest in the structural design of electromagnetic launchers. Cascade design electromagnetic launcher pressure vessels offer convenient maintenance access to high wear rate components of the structure while satisfying an unusual combination of electromagnetic, strength, and preloading constraints imposed on the system designer. This analysis for design of such structures focuses on the accurate characterization of fluid-structure interaction under dynamic asymmetric loading.

  17. Parallel rail electromagnetic launcher with multiple current path armature

    SciTech Connect

    Kemeny, G. A.

    1984-12-04

    Electromagnetic projectile launchers utilize multiple current path armatures in an internally series augmented conductor rail configuration or an internally augmented system connected to multiple power supplies. The current paths include plasmas, conductors or combinations of both. Plasma separation is maintained by trailing insulating plasma dividers extending toward the launcher breech from arc driving faces on a projectile sabot. Arc length and/or plama volume is reduced by conductive assemblies adjacent to the arc driving faces.

  18. Computational model for simulation small testing launcher, technical solution

    SciTech Connect

    Chelaru, Teodor-Viorel; Cristian, Barbu; Chelaru, Adrian

    2014-12-10

    The purpose of this paper is to present some aspects regarding the computational model and technical solutions for multistage suborbital launcher for testing (SLT) used to test spatial equipment and scientific measurements. The computational model consists in numerical simulation of SLT evolution for different start conditions. The launcher model presented will be with six degrees of freedom (6DOF) and variable mass. The results analysed will be the flight parameters and ballistic performances. The discussions area will focus around the technical possibility to realize a small multi-stage launcher, by recycling military rocket motors. From technical point of view, the paper is focused on national project 'Suborbital Launcher for Testing' (SLT), which is based on hybrid propulsion and control systems, obtained through an original design. Therefore, while classical suborbital sounding rockets are unguided and they use as propulsion solid fuel motor having an uncontrolled ballistic flight, SLT project is introducing a different approach, by proposing the creation of a guided suborbital launcher, which is basically a satellite launcher at a smaller scale, containing its main subsystems. This is why the project itself can be considered an intermediary step in the development of a wider range of launching systems based on hybrid propulsion technology, which may have a major impact in the future European launchers programs. SLT project, as it is shown in the title, has two major objectives: first, a short term objective, which consists in obtaining a suborbital launching system which will be able to go into service in a predictable period of time, and a long term objective that consists in the development and testing of some unconventional sub-systems which will be integrated later in the satellite launcher as a part of the European space program. This is why the technical content of the project must be carried out beyond the range of the existing suborbital vehicle

  19. Calculations supporting HyperVelocity Launcher development

    SciTech Connect

    Trucano, T.G.; Chhabildas, L.C.

    1993-08-01

    Sandia National Laboratories has developed a HyperVelocity Launcher (also referred to as HVL) in which a thin flier plate (nominally 1 mm thick) is launched to velocities in excess of 12 km/s. The length to diameter ratio of these launched flier plates varies from 0.02 to 0.06. The launch technique is based upon using structured, time-dependant, high-pressure, high-acceleration pulses to drive the flier plates. Such pulses are achieved by using a graded-density material to impact a stationary flier. A computational and experimental program at Sandia seeks to extend this technique to allow launching thick plates whose length-to-diameter ratio is 10 to 20 times larger than thin plates. Hydrodynamic codes are used to design modifications to the basic technique. The authors have controlled and used these effects to successfully launch a chunk-flier, consisting of 0.33 gm of titanium alloy, 0.3 cm thick by 0.6 cm in diameter, to a velocity of 10.2 km/s. This is the largest chunky size ever launched at this velocity from a gas gun configuration.

  20. Sharp and the Jules Verne Launcher

    SciTech Connect

    Hunter, J.; Cartland, H.

    1996-03-01

    Lawrence Livermore National Laboratory (LLNL) has built the worlds largest hydrogen gas gun called SHARP, (Super High Altitude Research Project). Originally designed to launch 5 kg to a 450 km altitude, SHARP is configured horizontally at Site 300 in Tracy, California. SHARP is successfully delivering 5 kg scramjets at Mach 9 in aerophysics tests. Some of the results of the scramjet tests are enlightening and are presented insofar as they are relevant to future launches into space. Using a light gas gun to launch payloads into orbit has been analyzed. We look at LEO (Low Earth Orbit), GEO (Geosynchronous Earth Orbit), and LO (Lunar Orbit). We present a conceptual design for a large light gas gun called the Jules Verne Launcher (JVL). The JVL can deliver 3.3 metric tons to a 500 km low earth orbit. We anticipate one launch per day. We present the history of light gas guns, the SHARP design and performance, and the JVL design. Another section is devoted to the vehicle environment and resultant design. Lastly, we present a cost analysis. Our results indicated that the JVL will be able to deliver 1000 metric tons of payload to LEO yearly. The cost will be 5{percent} of the best US rocket delivery cost. This technology will enable the next phase of man{close_quote}s exploration of space. {copyright} {ital 1996 American Institute of Physics.}

  1. Calibrating Accelerometers Using an Electromagnetic Launcher

    SciTech Connect

    Erik Timpson

    2012-05-13

    A Pulse Forming Network (PFN), Helical Electromagnetic Launcher (HEML), Command Module (CM), and Calibration Table (CT) were built and evaluated for the combined ability to calibrate an accelerometer. The PFN has a maximum stored energy of 19.25 kJ bank and is fired by a silicon controlled rectifier (SCR), with appropriate safety precautions. The HEML is constructed out of G-10 fiberglass and is designed to accelerate 600 grams to 10 meters per second. The CM is microcontroller based running Arduino Software. The CM has a keypad input and 7 segment outputs of the bank voltage and desired voltage. After entering a desired bank voltage, the CM controls the charge of the PFN. When the two voltages are equal it allows the fire button to send a pulse to the SCR to fire the PFN and in turn, the HEML. The HEML projectile's tip hits a target that is held by the CT. The CT consists of a table to hold the PFN and HEML, a vacuum chuck, air bearing, velocity meter and catch pot. The Target is held with the vacuum chuck awaiting impact. After impact, the air bearing allows the target to fall freely for the velocity meter to get an accurate reading. A known acceleration is determined from the known change in velocity of the target. Thus, if an accelerometer was attached to the target, the measured value can be compared to the known value.

  2. Commercial space development needs cheap launchers

    NASA Astrophysics Data System (ADS)

    Benson, James William

    1998-01-01

    SpaceDev is in the market for a deep space launch, and we are not going to pay $50 million for it. There is an ongoing debate about the elasticity of demand related to launch costs. On the one hand there are the ``big iron'' NASA and DoD contractors who say that there is no market for small or inexpensive launchers, that lowering launch costs will not result in significantly more launches, and that the current uncompetitive pricing scheme is appropriate. On the other hand are commercial companies which compete in the real world, and who say that there would be innumerable new launches if prices were to drop dramatically. I participated directly in the microcomputer revolution, and saw first hand what happened to the big iron computer companies who failed to see or heed the handwriting on the wall. We are at the same stage in the space access revolution that personal computers were in the late '70s and early '80s. The global economy is about to be changed in ways that are just as unpredictable as those changes wrought after the introduction of the personal computer. Companies which fail to innovate and keep producing only big iron will suffer the same fate as IBM and all the now-extinct mainframe and minicomputer companies. A few will remain, but with a small share of the market, never again to be in a position to dominate.

  3. Sharp and the Jules Verne Launcher

    NASA Astrophysics Data System (ADS)

    Hunter, John; Cartland, Harry

    1996-03-01

    Lawrence Livermore National Laboratory (LLNL) has built the worlds largest hydrogen gas gun called SHARP, (Super High Altitude Research Project). Originally designed to launch 5 kg to a 450 km altitude, SHARP is configured horizontally at Site 300 in Tracy, California. SHARP is successfully delivering 5 kg scramjets at Mach 9 in aerophysics tests. Some of the results of the scramjet tests are enlightening and are presented insofar as they are relevant to future launches into space. Using a light gas gun to launch payloads into orbit has been analyzed. We look at LEO (Low Earth Orbit), GEO (Geosynchronous Earth Orbit), and LO (Lunar Orbit). We present a conceptual design for a large light gas gun called the Jules Verne Launcher (JVL). The JVL can deliver 3.3 metric tons to a 500 km low earth orbit. We anticipate one launch per day. We present the history of light gas guns, the SHARP design and performance, and the JVL design. Another section is devoted to the vehicle environment and resultant design. Lastly, we present a cost analysis. Our results indicated that the JVL will be able to deliver 1000 metric tons of payload to LEO yearly. The cost will be 5% of the best US rocket delivery cost. This technology will enable the next phase of man's exploration of space.

  4. An Ergonomic Evaluation of the Extravehicular Mobility Unit (EMU) Space Suit Hard Upper Torso (HUT) Size Effect on Metabolic, Mobility, and Strength Performance

    NASA Technical Reports Server (NTRS)

    Reid, Christopher; Harvill, Lauren; England, Scott; Young, Karen; Norcross, Jason; Rajulu, Sudhakar

    2014-01-01

    The objective of this project was to assess the performance differences between a nominally sized Extravehicular Mobility Unit (EMU) space suit and a nominal +1 (plus) sized EMU. Method: This study evaluated suit size conditions by using metabolic cost, arm mobility, and arm strength as performance metrics. Results: Differences between the suit sizes were found only in shoulder extension strength being 15.8% greater for the plus size. Discussion: While this study was able to identify motions and activities that were considered to be practically or statistically different, it does not signify that use of a plus sized suit should be prohibited. Further testing would be required that either pertained to a particular mission critical task or better simulates a microgravity environment that the EMU suit was designed to work in.

  5. 6. DETAIL OF DRIVE TRUCK ASSEMBLY. MOBILE SERVICE STRUCTURE SPANNING ...

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

    6. DETAIL OF DRIVE TRUCK ASSEMBLY. MOBILE SERVICE STRUCTURE SPANNING LAUNCHER BUILDING WITH FLAME DUCT FAR RIGHT; VIEW TO NORTHWEST. - Cape Canaveral Air Station, Launch Complex 17, Facility 28416, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

  6. Blocked edges on Eulerian maps and mobiles: application to spanning trees, hard particles and the Ising model

    NASA Astrophysics Data System (ADS)

    Bouttier, J.; Di Francesco, P.; Guitter, E.

    2007-07-01

    We introduce Eulerian maps with blocked edges as a general way to implement statistical matter models on random maps by a modification of intrinsic distances. We show how to code these dressed maps by means of mobiles, i.e. decorated trees with labelled vertices, leading to a closed system of recursion relations for their generating functions. We discuss particular solvable cases in detail, as well as various applications of our method to several statistical systems such as spanning trees on quadrangulations, mutually excluding particles on Eulerian triangulations or the Ising model on quadrangulations.

  7. A preliminary study of pulse-laser powered orbital launcher

    NASA Astrophysics Data System (ADS)

    Katsurayama, Hiroshi; Komurasaki, Kimiya; Arakawa, Yoshihiro

    2009-10-01

    An air-breathing pulse-laser powered orbital launcher has been proposed as an alternative to conventional chemical launch systems. The aim of the present study is to assess its feasibility through the estimation of its achievable payload mass per unit beam power and launch cost. A transfer trajectory from the ground to a geosynchronous Earth orbit (GEO) is proposed, and the launch trajectory to its geosynchronous transfer orbit (GTO) is computed using the realistic performance modeled in the pulsejet, ramjet, and rocket flight modes of the launcher. Results show that the launcher can transfer 0.084 kg of payload per 1 MW beam power to a geosynchronous earth orbit. The cost becomes a quarter of existing systems if one can divide a single launch into 24,000 multiple launches.

  8. Exploratory development of the reconnection launcher, 1986--1990

    SciTech Connect

    Cowan, M.; Widner, M.M.; Cnare, E.C.; Duggin, B.W.; Kaye, R.J.; Freeman, J.R.

    1990-01-01

    We briefly summarize the exploratory development phase for the reconnection launcher. This is an induction launcher which features a contactless, solid armature with either flat-plate or cylindrical geometry. The strategy for successful design is discussed, emphasizing the way we resolve the issues of ohmic heating and high-voltage requirements for high velocity. The indispensable role of a fast-running, mesh-matrix code is stressed. We describe three multistage launchers. One of these achieved muzzle velocity of 1 km/s with a 150-gram flat-plate projectile. The other two have launched cylindrical projectiles at 335 m/s, one with relatively heavy projectiles of 5 kg, the other with relatively light ones of 10 grams. The cylindrical projectiles can be spin-stabilized prior to launch for improved flight. We outline the potential of this technology for earth-to-orbit launch of small satellites. 19 refs., 9 figs.

  9. Exploratory development of the reconnection launcher 1986-1990

    SciTech Connect

    Cowan, M.; Widner, M.M.; Cnare, E.C.; Duggin, B.W.; Kaye, R.J.; Freeman, J.R. )

    1991-01-01

    This paper summarizes the exploratory development phase for the reconnection launcher. This is an induction launcher which features a contractless, solid armature with either flat-plate or cylindrical geometry. The strategy for successful design is discussed, emphasizing the way we resolve the issues of ohmic heating and high-voltage requirements for high velocity. The indispensable role of a fast-running, mesh-matrix code is stressed. The authors describe three multistage launchers. One of these achieved muzzle velocity of 1 km/s with a 150-gram flat-plate projectile. The other two have launched cylindrical projectiles at 335 m/s, one with relatively heavy projectiles of 5 kg, the other with relatively light ones of 10 grams. The cylindrical projectiles can be spin-stabilized prior to launch for improved flight. We outline the potential of this technology for earth-to-orbit launch of small satellites.

  10. Direct Energy Exchange Enhancement in Distributed Injection Light Gas Launchers

    SciTech Connect

    Alger, T W; Finucane, R G; Hall, J P; Penetrante, B M; Uphaus, T M

    2000-04-06

    It is not widely acknowledged or appreciated that conventional, two-stage light-gas launchers do not efficiently apply their high breech pressures to the design intent: accelerating the projectile. Our objective in this project was to carry out the analysis, design, construction, and testing of a new class of launchers that will address this limitation. Our particular application is to expand the pressure range of the conventional, two-stage gas launcher to overlap and validate the pressure regimes previously attainable only with shock waves generated by nuclear explosions, lasers, or multistage conventional explosions. That is, these launchers would have the capability to conduct--in a laboratory setting--high-velocity-impact, equation-of-state (EOS) measurements at up to 2-TPa (20 Mbar) pressure levels in high-Z materials. Our design entailed a new class of distributed-injection, gas-dynamic launchers that are designed to use a boat-tail projectile to overcome the fundamental gas-expansion phenomena known as escape velocity (the Riemann limit). Our program included analytical, numerical, and experimental studies of the fast gas release flow technique that is central to the success of our approach. The analyses led us to believe that, in a typical configuration, the pressure will be effectively applied to the projectile in a time short relative to its few-microsecond traverse time; the experimental program we conducted during FY1999 supported these estimates. In addition, our program revealed dramatic increased efficiency in this process that was previously unknown to the launcher community. The most fundamental practical restrictions on the performance of any gas launcher are the ability of the launcher to (1) contain pressure in a reservoir, and (2) effectively apply that pressure to the base of a moving projectile. Our gas-release test-fixture experiments showed that our design was capable of applying nearly twice the pressure to the projectile that is

  11. 11. 28'X40' original vellum, VariableAngle Launcher, 'INDEX TO Drawings' drawn ...

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

    11. 28'X40' original vellum, Variable-Angle Launcher, 'INDEX TO Drawings' drawn at no scale (P.W.DWG.No. 1781). - Variable Angle Launcher Complex, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  12. 10. 28'X40' original vellum, VariableAngle Launcher, 'PROJECT PLOT PLAN' drawn ...

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

    10. 28'X40' original vellum, Variable-Angle Launcher, 'PROJECT PLOT PLAN' drawn at no scale (P.W.DWG.NO. 1781). - Variable Angle Launcher Complex, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  13. 9. 22'X34' original vellum, VariableAngle Launcher, 'GENERAL SITE PLAN' drawn ...

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

    9. 22'X34' original vellum, Variable-Angle Launcher, 'GENERAL SITE PLAN' drawn at 1'=200'. (BUORD Sketch # 209887, PAPW 300). - Variable Angle Launcher Complex, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  14. Modes Interactions Due to Launcher Dynamic Behavior Variations During Flight

    NASA Astrophysics Data System (ADS)

    Foucaud, Simon; Gonidou, Luc-Olivier; Daniel, Jerome; Escudero, Luis

    2014-06-01

    Due to propellant consumption, mass and stiffness properties of a launcher are varying in a very wide range in a relatively short time. Consequently, dynamic behavior and first bending modes of the launcher are varying during the flight. This time evolutions can lead to modes interactions with potential impacts on launcher control. The prediction of modal behavior for all instants requires a strong effort of modelling and high computing cost using a classical finite element modelling (FEM) approach. An alternative method with relatively low computational costs has been developed in order to cover a large number of time instants. The approach considers a reference modal basis at a given time as a starting point and then derives the whole flight modal properties using mass and stiffness variations only.This paper intends to present the method and its applications. In a first step, the theoretical aspect of the method is described and results are shown in comparison with FEM results. The method reveals its ability to catch modal interactions occurring in-between reference time instants. Secondly, the method is coupled to a parametric tool in order to estimate the impact of payloads or supporting structures characteristics on launcher excitabilities. Finally, outputs are presented as three-dimensional maps representing launcher excitabilities with respect to time and frequency for a "cloud" of payloads. Results are presented for the next evolution of ARIANE 5 - so called A5ME version. The method gives an overview of the mechanical and piloting excitabilities of the A5ME launcher for a wide flight domain. This is a very powerful tool for estimating the validity of other dimensioning methodologies and the associated margins.

  15. Flow Field Analysis of a Future Launcher Configuration during Start

    NASA Astrophysics Data System (ADS)

    Bozic, O.; Otto, H.

    2005-02-01

    Within the German Future Space Launcher Technology Research Program ASTRA several reusable concepts have been investigated. Particularly one dedicated for near-term application consists of an Ariane 5-type expendable core stage and two liquid fly back boosters (LFBB). The present investigation focused on the interaction between the booster and the core stage during ascent phase. The analysis is carried out numerically by means of the DLR unstructured code TAU. The numerical results allow a compressive study of the complicate flow pattern between the boosters and the central core and address the changes on aerodynamic drag between the three configurations considered. Key words: launcher, ASTRA, LFBB, flow simulation, CFD simulation, unstructured grid

  16. Metal vapor vacuum arc switching - Applications and results. [for launchers

    NASA Technical Reports Server (NTRS)

    Cope, D.; Mongeau, P.

    1984-01-01

    The design of metal-vapor vacuum-arc switches (MVSs) for electromagnetic launchers is discussed, and preliminary results are presented for an experimental MVS. The general principles of triggered-vacuum-gap and vacuum-interrupter MVSs are reviewed, and the requirements of electromagnetic launchers are analyzed. High-current design problems such as electrode erosion, current sharing, magnetic effects, and thermal effects are examined. The experimental MVS employs stainless-steel flanges, a glass vacuum vessel, an adjustable electrode gap, autonomous internal magnetic-field coils, and a tungsten-pin trigger assembly. Some results from tests without magnetic augmentation are presented graphically.

  17. Mesh-matrix analysis method for electromagnetic launchers

    NASA Technical Reports Server (NTRS)

    Elliott, David G.

    1989-01-01

    The mesh-matrix method is a procedure for calculating the current distribution in the conductors of electromagnetic launchers with coil or flat-plate geometry. Once the current distribution is known the launcher performance can be calculated. The method divides the conductors into parallel current paths, or meshes, and finds the current in each mesh by matrix inversion. The author presents procedures for writing equations for the current and voltage relations for a few meshes to serve as a pattern for writing the computer code. An available subroutine package provides routines for field and flux coefficients and equation solution.

  18. 96. 28'X40' original vellum, VariableAngle Launcher '32 INCH TUBE ASSEMBLY ...

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

    96. 28'X40' original vellum, Variable-Angle Launcher '32 INCH TUBE ASSEMBLY SECTION 1' drawn at 3'=1'-0', 6'=1'-0', and full size. (P.W. DWG. NO. 1783). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  19. 91. 22'X34' original blueprint, VariableAngle Launcher, 'CONNECTING BRIDGE, REAR VIEW ...

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

    91. 22'X34' original blueprint, Variable-Angle Launcher, 'CONNECTING BRIDGE, REAR VIEW CAMERA HOUSE ASSEMBLY' drawn at 3/8=1'-0', 3'=1'-0'. (BUORD Sketch # 209042). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  20. 87. 22'X34' original vellum, VariableAngle Launcher 'WEST ELEVATION AND PLANMAIN ...

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

    87. 22'X34' original vellum, Variable-Angle Launcher 'WEST ELEVATION AND PLAN-MAIN STRUCTURE' drawn at 1'=10'. (BUORD Sketch # 207648, PAPW 1832). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  1. 99. 28'X40' original vellum, VariableAngle Launcher '32 INCH 'Y' JOINT ...

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

    99. 28'X40' original vellum, Variable-Angle Launcher '32 INCH 'Y' JOINT DETAILS drawn at 1 1/2'=1'-0' and 6'=1'-0'. (P.W. DWG. NO. 1786). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  2. 101. 28'X40' original vellum, VariableAngle Launcher '32 INCH BREECH DOOR ...

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

    101. 28'X40' original vellum, Variable-Angle Launcher '32 INCH BREECH DOOR OPERATING MECHANISM ASSEMBLY' drawn at 3'=1'-0, 6'=1'0', and full size. (P.W. DRW. NO. 1788). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  3. 98. 28'X40' original vellum, VariableAngle Launcher '32 INCH 'Y' JOINT ...

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

    98. 28'X40' original vellum, Variable-Angle Launcher '32 INCH 'Y' JOINT AND TRANSITION ASSEMBLY' drawn at 1 1/2'=1'-0'. (P.W. DWG. NO. 1785). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  4. 100. 28'X40' original vellum, VariableAngle Launcher '32 INCH BREECH' drawn ...

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

    100. 28'X40' original vellum, Variable-Angle Launcher '32 INCH BREECH' drawn at 2'=1'-0', 3'=1'-0' and full size. (P.W. DWG. NO. 1787). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  5. 86. 22'X34' original vellum, VariableAngle Launcher 'GENERAL PLAN AND ELEVATION' ...

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

    86. 22'X34' original vellum, Variable-Angle Launcher 'GENERAL PLAN AND ELEVATION' drawn at 1'=40'. (BUORD Sketch # 207184, PAPW 1892). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  6. 88. 22'X34' original vellum, VariableAngle Launcher 'EAST ELEVATION AND PLAN ...

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

    88. 22'X34' original vellum, Variable-Angle Launcher 'EAST ELEVATION AND PLAN MAIN STRUCTURE' drawn at 1'=10'. (BUORD Sketch # 207572, PAPW 1833) - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  7. 97. 28'X40' original vellum, VariableAngle Launcher '32 INCH UPPER TUBE ...

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

    97. 28'X40' original vellum, Variable-Angle Launcher '32 INCH UPPER TUBE ASSEMBLY' drawn at 2'=1'-0' and 6'=1'0', full size. (P.W. DWG. NO. 1784). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  8. 93. 22'X34' original blueprint, VariableAngle Launcher, 'OVERHEAD CAMERA SUSPENSION SYSTEM, ...

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

    93. 22'X34' original blueprint, Variable-Angle Launcher, 'OVERHEAD CAMERA SUSPENSION SYSTEM, TOWER STAY CABLES' drawn at 3/4'=1'-0'. (BUORD Sketch # 208783). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  9. 92. 22'X34' original blueprint, VariableAngle Launcher, 'CAMERA CABLE TOWER PLAN ...

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

    92. 22'X34' original blueprint, Variable-Angle Launcher, 'CAMERA CABLE TOWER PLAN AND ELEVATION' drawn at 3/8'=1'0' (BUORD Sketch # 208580). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  10. 95. 28'X40' original vellum, VariableAngle Launcher '32 INCH TUBE ASSEMBLY' ...

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

    95. 28'X40' original vellum, Variable-Angle Launcher '32 INCH TUBE ASSEMBLY' drawn at 1/8'=1'-0', 1'=1'-0' and 1'-40'. (P.W. DWG. NO. 1782). - Variable Angle Launcher Complex, Variable Angle Launcher, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  11. Inductiveless Rail Launchers for Long Projectiles

    DTIC Science & Technology

    2001-04-26

    railgun concept is not readily applicable to tactical guns because it is hard to integrate sizable storage capacitors into the barrel . To circumvent... barrel . However, the total weight of such numerous cables (each transmitting only a very short pulse of the full high current) appears to be...switching losses. 284 Completing the description of inductiveless launch tubes, Fig. 9 depicts a steel tubular shell, or barrel . Its function is to house the

  12. Mobilization

    DTIC Science & Technology

    1987-01-01

    istic and romantic emotionalism that typifies this genre. Longino, James C., et al. “A Study of World War Procurement and Industrial Mobilization...States. Harrisburg, PA: Military Service Publishing Co., 1941. CARL 355.22 J72b. Written in rough prose , this World War II era document explains the

  13. STS-32 Columbia, OV-102, is positioned on the hard stand at KSC LC Pad 39A

    NASA Image and Video Library

    1989-11-28

    S89-51983 (18 Nov 1989) --- Roll-out of the Space Shuttle Columbia is completed as the vehicle, atop the Mobile Launcher Platform, is positioned on the hard stand at Pad 39A. The approximately eight-hour journey from the Vehicle Assembly Building began at 2:32 a.m. EST. This marks the first time a Space Shuttle has been at Pad A at Launch Complex 39 since January 12, 1986, when Columbia was launched on mission 61C. Pad A will next be used for the launch of Columbia and a five person crew on the STS-32 mission, presently scheduled for no earlier than December 18, 1989.

  14. Note Launchers: Promoting Active Reading of Mathematics Textbooks

    ERIC Educational Resources Information Center

    Helms, Josh W.; Helms, Kimberly Turner

    2010-01-01

    Note launchers, an instructor-designed reading guide, model how to select, decide, and focus upon what textbook material is important to learn. Reading guides are specially-designed study aids that can steer students through difficult parts of assigned readings (Bean, 1996) while encouraging advance preparation. As an example of a reading guide,…

  15. Dynamics of a medieval missile launcher: the trebuchet

    NASA Astrophysics Data System (ADS)

    O'Connell, James

    2001-11-01

    In the Middle Ages, the heavy throw-weight launcher of choice was the trebuchet. When the heavy mass, attached to the short end of the pivoted beam, is released and falls, the projectile, which is in a sling fastened to the other end of the beam, begins to acquire a high velocity.

  16. 58. VIEW OF SOUTHWEST SIDE OF LAUNCHER FROM ABOVE. AFRAME ...

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

    58. VIEW OF SOUTHWEST SIDE OF LAUNCHER FROM ABOVE. A-FRAME PIVOT POINT IN CENTER OF PHOTOGRAPH; NITROGEN CONTROL UNIT IN UPPER LEFT CORNER OF PHOTOGRAPH. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  17. 13. Photocopy of drawing of missile launcher from 'Procedures and ...

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

    13. Photocopy of drawing of missile launcher from 'Procedures and Drills for the NIKE Ajax System,' Department of the Army Field Manual, FM-44-80 from Institute for Military History, Carlisle Barracks, Carlisle, PA, 1956 - NIKE Missile Battery PR-79, East Windsor Road south of State Route 101, Foster, Providence County, RI

  18. Energy stores and switches for rail-launcher systems

    NASA Technical Reports Server (NTRS)

    Weldon, W. F.; Zowarka, R. C.; Marshall, R. A.

    1983-01-01

    An overview of existing switch and power supply technology applicable to space launch, a new candidate pulsed power supply for Earth-to-space rail launcher duty, the inverse railgun flux compressor, and a set of switching experiments to study further the feasibility of Earth-to-space launch are discussed.

  19. 48. CONTROL PANEL FOR UMBILICAL MAST AND TRENCH DOORS. LAUNCHER ...

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

    48. CONTROL PANEL FOR UMBILICAL MAST AND TRENCH DOORS. LAUNCHER ON RIGHT IN BACKGROUND; TRENCH DOORS AND RAIL BEHIND CONTROL PANEL - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  20. An Engineering Design STEM Project: T-Shirt Launcher

    ERIC Educational Resources Information Center

    Fantz, Todd D.; Grant, Melva R.

    2013-01-01

    The article offers information on making technology education students interested in science and mathematics through the use of a T-shirt launcher design project. This project was designed for junior and senior level high school students who have completed or are currently taking physics and precalculus. The project involves designing an…

  1. RLV candidates for European Future Launchers Preparatory Programme

    NASA Astrophysics Data System (ADS)

    Tomatis, Carlo; Bouaziz, Laurent; Franck, Thomas; Kauffmann, Jens

    2009-07-01

    ESA's Future Launcher Preparatory Programme (FLPP) includes system activities and technology developments on materials and structures and propulsion. The overall approach is system-driven, i.e. FLPP aims at defining reference launcher concepts from which will be derived a demonstration logic including in-flight experimental vehicles, and technology development requirements. The paper addresses the launcher concepts studies, and more specifically the analysis of Reusable Launch Vehicle (RLV) concepts that has been performed in the first part of the FLPP program. The paper provides first elements on the mission requirements, the operations and the ground facilities for the RLV concepts selected as potential FLPP candidates. In particular, operations will likely have a heavy impact on the operability and on the launch cost of RLVs; in this sense, most of the paper content is dedicated to discuss specific operation features, and related infrastructure elements, linked to the considered RLVs. At last, a brief presentation of the next steps of the launcher system activities inside the FLPP is given.

  2. 63. VIEW OF FLAME BUCKET AND LAUNCHER FROM SOUTHEAST. TRICHLOROETHENE ...

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

    63. VIEW OF FLAME BUCKET AND LAUNCHER FROM SOUTHEAST. TRICHLOROETHENE RECOVERY TANK LEFT OF FLAME BUCKET; LIQUID OXYGEN CATCH TANK RIGHT OF FLAME BUCKET. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Pad 3 East, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

  3. Feasibility study of superconducting LSM rocket launcher system

    NASA Technical Reports Server (NTRS)

    Yoshida, Kinjiro; Ohashi, Takaaki; Shiraishi, Katsuto; Takami, Hiroshi

    1994-01-01

    A feasibility study is presented concerning an application of a superconducting linear synchronous motor (LSM) to a large-scale rocket launcher, whose acceleration guide tube of LSM armature windings is constructed 1,500 meters under the ground. The rocket is released from the linear launcher just after it gets to a peak speed of about 900 kilometers per hour, and it flies out of the guide tube to obtain the speed of 700 kilometers per hour at the height of 100 meters above ground. The linear launcher is brought to a stop at the ground surface for a very short time of 5 seconds by a quick control of deceleration. Very large current variations in the single-layer windings of the LSM armature, which are produced at the higher speed region of 600 to 900 kilometers per hour, are controlled successfully by adopting the double-layer windings. The proposed control method makes the rocket launcher ascend stably in the superconducting LSM system, controlling the Coriolis force.

  4. Characteristics of a large multijunction launcher for high-power LHCD experiments on JT-60U

    SciTech Connect

    Seki, M.; Ikeda, Y.; Ushigusa, K.; Naito, O.; Kondoh, T.; Wolfe, S.W.; Imai, T. )

    1994-10-15

    This paper presents overview of a large multijunction launcher for JT-60U. The launcher is featured by the multijunction module with the oversized taper waveguide, in order to simplify structure of the launcher. This launcher allows high performances of current drive and current profile control by using very sharp and highly directive spectrum. Initial result of coupling property is also described. A good coupling was observed at a power level of [similar to]0.8 MW with plasma-launcher distance of [lt]14 cm.

  5. Hardness testing

    SciTech Connect

    Not Available

    1987-01-01

    This technical manual is a handbook dealing with all aspects of hardness testing. Every hardness testing method is fully covered, from Rockwell to ultrasonic hardness testing. Specific hardness testing problems are also discussed, and methods are offered for many applications. One chapter examines how to select the correct hardness testing method. A directory of manufacturers, distributors and suppliers of hardness testing equipment and supplies in the United States and Canada is also included. The book consist of eight chapters and an appendix. It discusses common concepts of hardness, and the theories and methods of hardness testing. Coverage includes specific hardness testing methods - Brinell, Rockwell, Vickers, and microhardness testing; and other hardness testing methods, such as scleroscope, ultrasonic, scratch and file testing, and hardness evaluation by eddy current testing.

  6. Mode Launcher Design for the Multi-moded DLDS

    SciTech Connect

    Li, Zenghai

    2003-04-30

    The DLDS (Delay Line Distribution System) power delivery system proposed by KEK combines several klystrons to obtain the high peak power required to drive a TeV scale linear collider. In this system the combined klystron output is subdivided into shorter pulses by proper phasing of the sources, and each subpulse is delivered to various accelerator sections via separate waveguides. A cost-saving improvement suggested by SLAC is to use a single multimoded waveguide to deliver the power of all the subpulses. This scheme requires a mode launcher that can deliver each subpulse by way of a different waveguide mode through selective phasing of the sources when combining their power. We present a compact design for such a mode launcher that converts the power from four rectangular waveguide feeds to separate modes in a multi-moded circular guide through coupling slots. Such a design has been simulated and found to satisfy the requirements for high efficiency and low surface fields.

  7. LAUNCHER PERFORMANCE IN THE DIII-D SYSTEM

    SciTech Connect

    KAJIWARA,K; BAXI,CB; LOHR,J; GORELOV,YA; GREEN,MT; PONCE,D; CALLIS,RW

    2003-07-01

    LAUNCHER PERFORMANCE IN THE DIII-D SYSTEM. The thermal performance of three different designs for the steerable mirrors on the ECH launchers installed in the DIII-D tokamak has been evaluated theoretically and experimentally. In each case the disruption forces must be minimized while providing a low loss reflecting surface. One design uses all Glidcop{reg_sign} material, but shaped so that the center is appreciably thicker than the edge. A second design is graphite with a molybdenum surface brazed to the graphite. The latest design is laminated copper/stainless steel construction with a thin copper reflecting surface. All three mirrors employ passive radiative cooling. The mirror temperatures are measured by resistance temperature devices (RTDs) which are attached at the back surfaces of the mirrors. The temperature increases are moderate for the laminated mirror, which has the best overall performance.

  8. Ethernet Networks for Real-Time Systems: Application to Launchers

    NASA Astrophysics Data System (ADS)

    Robert, Jeremy; Georges, Jean-Philippe; Divoux, Thierry; Miramont, Philippe; Rmill, Badr

    2011-08-01

    The present paper highlights the results obtained in CNES french Research & Technology activity. The objective of this study is to replace the historical serial data bus (MIL-STD 1553B) with a COTS (Components Off The Shelf) solution into a launcher as Ariane 5. As a matter of course, this solution must guarantee at least the same performances (real-time, reliability, etc). As a result this paper focuses on Ethernet standard. Nowadays, Ethernet is a consensual solution implemented in several domains as such industrial context (Jaguar, etc) or even avionics (Airbus A380). The paper highlights the first is- sues of the native Ethernet and its main evolutions which enable to embed an Ethernet network in a launcher, while ensuring real-time performances. Finally, a methodology is proposed to design an Ethernet reliable architecture.

  9. Design and Analysis of Steerable ECRH Launcher for SST-1 Tokamak

    NASA Astrophysics Data System (ADS)

    Mistry, Hardik; Shukla, B. K.

    2017-07-01

    In the tokamaks ECRH system is used for pre-ionization, start up, heating, current drive and suppression of NTMs (Neo Classical Tearing Modes). A Standard ECRH system consists of high power microwave source Gyrotron, circular corrugated waveguide based transmission line and launcher. The Focused ECH power is launched into plasma through launcher. The microwave beam emerges out from circular corrugated waveguide and propagates freely in air with finite divergence. So focusing and plane mirror combination is used to launch focused beam in plasma. Thus an ECRH launcher consists of metallic profiled and plane mirror, UHV compatible vacuum barrier window and a UHV gate valve. One 42 GHz gyrotron capable of delivering 500 kW of power for 500 ms and other 82 GHz gyrotron capable of delivering 200 kW of power for 1000s are used for SST-1 ECRH system. The launcher design consists of mirror design, design of supports and design of steering mechanism to provide suitable movements with minimum backless error. The whole assembly is UHV compatible. The launcher is capable of steering the beams by ±20° in both toroidal and poloidal directions. Mirrors are given motion by means of one rotary and one linear feedthrough. For 82 GHz launcher active cooling is provided, whereas for 42 GHz launcher no active cooling is provided. A detailed analysis is carried out for the mirrors of the high power launcher. The heat load for the 82 GHz launcher is 2 kW ( 1% absorption) and for 42 GHz launcher it is 5 kW. For 82 GHz launcher, the maximum steady state surface temperatures of focusing and reflecting mirrors are 315K and 323K and von-mises stresses are within 10 MPa. Similarly for 42 GHz launcher maximum temperatures observed during 500 ms pulse are 301K and 303K for focusing and reflecting mirrors respectively. This paper explains the mechanical and thermal design and analysis of the launcher for the ECRH system.

  10. Resonant Inductive Power Transfer for Noncontact Launcher-Missile Interface

    DTIC Science & Technology

    2016-08-01

    implementation of a wireless power transfer system based on the concept of non-radiating inductive coupling. 14. SUBJECT TERMS Resonant Inductive Coupling...the purpose of a wireless power transfer system based on the concept of nonradiating inductive coupling. The core of the system is the inductive...TECHNICAL REPORT RDMR-WD-16-37 RESONANT INDUCTIVE POWER TRANSFER FOR NONCONTACT LAUNCHER-MISSILE INTERFACE Martin S

  11. Variable dual-frequency electrostatic wave launcher for plasma applications

    NASA Astrophysics Data System (ADS)

    Jorns, Benjamin; Sorenson, Robert; Choueiri, Edgar

    2011-12-01

    A variable tuning system is presented for launching two electrostatic waves concurrently in a magnetized plasma. The purpose of this system is to satisfy the wave launching requirements for plasma applications where maximal power must be coupled into two carefully tuned electrostatic waves while minimizing erosion to the launching antenna. Two parallel LC traps with fixed inductors and variable capacitors are used to provide an impedance match between a two-wave source and a loop antenna placed outside the plasma. Equivalent circuit analysis is then employed to derive an analytical expression for the normalized, average magnetic flux density produced by the antenna in this system as a function of capacitance and frequency. It is found with this metric that the wave launcher can couple to electrostatic modes at two variable frequencies concurrently while attenuating noise from the source signal at undesired frequencies. An example based on an experiment for plasma heating with two electrostatic waves is used to demonstrate a procedure for tailoring the wave launcher to accommodate the frequency range and flux densities of a specific two-wave application. This example is also used to illustrate a method based on averaging over wave frequencies for evaluating the overall efficacy of the system. The wave launcher is shown to be particularly effective for the illustrative example—generating magnetic flux densities in excess of 50% of the ideal case at two variable frequencies concurrently—with a high adaptability to a number of plasma dynamics and heating applications.

  12. Variable dual-frequency electrostatic wave launcher for plasma applications.

    PubMed

    Jorns, Benjamin; Sorenson, Robert; Choueiri, Edgar

    2011-12-01

    A variable tuning system is presented for launching two electrostatic waves concurrently in a magnetized plasma. The purpose of this system is to satisfy the wave launching requirements for plasma applications where maximal power must be coupled into two carefully tuned electrostatic waves while minimizing erosion to the launching antenna. Two parallel LC traps with fixed inductors and variable capacitors are used to provide an impedance match between a two-wave source and a loop antenna placed outside the plasma. Equivalent circuit analysis is then employed to derive an analytical expression for the normalized, average magnetic flux density produced by the antenna in this system as a function of capacitance and frequency. It is found with this metric that the wave launcher can couple to electrostatic modes at two variable frequencies concurrently while attenuating noise from the source signal at undesired frequencies. An example based on an experiment for plasma heating with two electrostatic waves is used to demonstrate a procedure for tailoring the wave launcher to accommodate the frequency range and flux densities of a specific two-wave application. This example is also used to illustrate a method based on averaging over wave frequencies for evaluating the overall efficacy of the system. The wave launcher is shown to be particularly effective for the illustrative example--generating magnetic flux densities in excess of 50% of the ideal case at two variable frequencies concurrently--with a high adaptability to a number of plasma dynamics and heating applications.

  13. Modeling the capillary discharge of an electrothermal (ET) launcher

    NASA Astrophysics Data System (ADS)

    Least, Travis

    Over the past few decades, different branches of the US Department of Defense (DoD) have invested at improving the field ability of electromagnetic launchers. One such focus has been on achieving hypervelocity launch velocities in excess of 7 km/s for direct launch to space applications [1]. It has been shown that pre-injection is required for this to be achieved. One method of pre-injection which has promise involves using an electro-thermal (ET) due to its ability to achieve the desired velocities with a minimal amount of hot plasma injected into the launcher behind the projectile. Despite the demonstration of pre-injection using this method, polymer ablation is not very well known and this makes it challenging to predict how the system will behave for a given input of electrical power. In this work, the rate of ablation has been studied and predicted using different models to generate the best possible characteristic curve. [1] - Wetz, David A., Francis Stefani, Jerald V. Parker, and Ian R. McNab. "Advancements in the Development of a Plasma-Driven Electromagnetic Launcher." IEEE TRANSACTIONS ON MAGNETICS 45.1 (2009): 495--500. IEEE Xplore. Web. 18 Aug. 2012.

  14. Space debris mitigation measures applied to European launchers

    NASA Astrophysics Data System (ADS)

    Bonnal, Christophe; Gigou, Jacques; Aubin, Didier

    2009-12-01

    In November 1986, more than 20 years ago, an H8 upper stage of Ariane 1 exploded in orbit nine months after the end of its mission. So as to avoid the generation of debris in low Earth orbit, a dedicated complementary development modified the design, introducing systematic passivation of the stage. Ever since this event, space debris mitigation has been a major concern for all launcher activities in Europe. After a short recall of the launchers currently operated by Arianespace as well as those currently developed by ESA with CNES, particularly for the safeguard authority, including the most promising future evolutions, the set of applicable regulations is described. These rules are fundamentally derived from the IADC Guidelines (hence the UNCOPUOS ones), translated into European Code of Conduct and in some more applicable Standards, such as the one prepared by ESA. The process of preparing ISO standards, mainly through the ECSS Working Group, is also described. Three major families can be identified: minimization of Mission Related Objects, Passivation of stages at the end of mission, and orbital protected zones including the so-called 25-year rule. The paper describes how European launchers do or will fulfill these applicable standards, quantifying the efficiency of the mitigation rules, and describing improvement actions currently under study.

  15. Propulsive jet influence on generic launcher base flow

    NASA Astrophysics Data System (ADS)

    Stephan, S.; Wu, J.; Radespiel, R.

    2015-12-01

    Afterbody flow phenomena represent a significant source of uncertainties in the design of a launcher. Therefore, there is a demand for measuring such flows in wind tunnels. For propulsive jet simulation a new jet facility was integrated into a hypersonic/supersonic wind tunnel. The jet simulation resembles the generic model of a staged rocket launcher. The design and the qualification of the facility are reported. This includes measurements of pressure, temperature and Mach number distribution. Pressure and Schlieren measurements are conducted in the wake of the generic launcher. The unsteady pressure characteristics at the generic rocket base and fairing are analyzed for supersonic and hypersonic freestream. The influence of the under-expanded jet is reported and the jet temperatures are varied. On the base fluctuations at a Strouhal number around 0.25 dominates supersonic freestream flows. Additionally, a fluctuation level increase on the base is observed for Strouhal numbers above 0.75 in hypersonic flow regime, which is attributed to the interactions of wake flow and jet.

  16. Projectile transverse motion and stability in electromagnetic induction launchers

    SciTech Connect

    Shokair, I.R.

    1993-08-01

    The transverse motion of a projectile in an electromagnetic induction launcher is considered. The equations of motion for translation and rotation are derived assuming a rigid projectile and a flyway restoring force per unit length that is proportional to the local displacement. Transverse forces and torques due to energized coils are derived for displaced or tilted projectile elements based on a first order perturbation method. The resulting equations of motion for a rigid projectile composed of multiple elements in a multi-coil launcher are analyzed as a coupled oscillator system of equations and a simple stability condition is derived. The equations of motion are incorporated into the 2-D Slingshot code and numerical solutions for the transverse motion are obtained. For the 20 meter navy launcher parameters we find that stability is achieved with a flyway spring constant of k {approx} 1{times} 10{sup 8} N/m{sup 2}. For k {approx} 1.5 {times} 10{sup 8} N/m{sup 2} and sample coil misalignment modeled as a sine wave of I mm amplitude at wavelengths of one or two meters, the projectile displacement grows to a maximum of 4 mm. This growth is due to resonance between the natural frequency of the Projectile transverse motion and the coil displacement wavelength. This resonance does not persist because of the changing axial velocity. Random coil displacement is also found to cause roughly the same projectile displacement. For the maximum displacement a rough estimate of the transverse pressure is 50 bars.

  17. Design of Launcher Towards Spacecraft Comfort: Ariane 6 Objectives

    NASA Astrophysics Data System (ADS)

    Mourey, Patrick; Lambare, Hadrien; Valbuena, Matias F.

    2014-06-01

    Preliminary advanced studies were performed recently to select the possible concepts for a launcher that could succeed to Ariane 5. During the end of 2012 Space Ministry Conference, a configuration defining the propellant of the stages and the coarse staging ("PPH") was frozen in order to engage the preliminary selection concept studies. The first phase consisted to select the main features of the architecture in order to go deeper in the different matters or the advanced studies. The concept was selected mid of 2013.During all these phases of the preliminary project, different criteria (such as the recurring cost which is a major one) were used to quote the different concepts, among which the "payload comfort", ie the minimization of the environment generated by the launcher toward the satellites.The minimization of the environment was first expressed in term of objectives in the Mission Requirement Document (MRD) for the different mechanical environment such as quasi-static loads, dynamic loads, acoustics, shocks... Criteria such as usable volume, satellites frequency requirement and interface requirement are also expressed in the MRD.The definition of these different criteria was of course fixed taking benefit from the launcher operator experience based on a long story of dealing with spacecraft-launcher interface issues on Ariane, Soyouz and Vega. The general idea is to target improved or similar levels than those currently applicable for Ariane 5. For some environment for which a special need is anticipated from the potential end users, a special effort is aimed.The preliminary advanced study phase is currently running and has to address specific topics such as the definition of the upper part layout including geometry ofthe fairing, the definition of the launch pad with preliminary ideas to minimize acoustics and blast wave or first calculations on dimensioning dynamic load- cases such as thrust oscillations of the solid rocket motors (SRM).The present paper

  18. Launcher Systems Development Cost: Behavior, Uncertainty, Influences, Barriers and Strategies for Reduction

    NASA Technical Reports Server (NTRS)

    Shaw, Eric J.

    2001-01-01

    This paper will report on the activities of the IAA Launcher Systems Economics Working Group in preparations for its Launcher Systems Development Cost Behavior Study. The Study goals include: improve launcher system and other space system parametric cost analysis accuracy; improve launcher system and other space system cost analysis credibility; and provide launcher system and technology development program managers and other decisionmakers with useful information on development cost impacts of their decisions. The Working Group plans to explore at least the following five areas in the Study: define and explain development cost behavior terms and concepts for use in the Study; identify and quantify sources of development cost and cost estimating uncertainty; identify and quantify significant influences on development cost behavior; identify common barriers to development cost understanding and reduction; and recommend practical, realistic strategies to accomplish reductions in launcher system development cost.

  19. Launcher Systems Development Cost: Behavior, Uncertainty, Influences, Barriers and Strategies for Reduction

    NASA Technical Reports Server (NTRS)

    Shaw, Eric J.

    2001-01-01

    This paper will report on the activities of the IAA Launcher Systems Economics Working Group in preparations for its Launcher Systems Development Cost Behavior Study. The Study goals include: improve launcher system and other space system parametric cost analysis accuracy; improve launcher system and other space system cost analysis credibility; and provide launcher system and technology development program managers and other decisionmakers with useful information on development cost impacts of their decisions. The Working Group plans to explore at least the following five areas in the Study: define and explain development cost behavior terms and concepts for use in the Study; identify and quantify sources of development cost and cost estimating uncertainty; identify and quantify significant influences on development cost behavior; identify common barriers to development cost understanding and reduction; and recommend practical, realistic strategies to accomplish reductions in launcher system development cost.

  20. Assessing the role of syringe dispensing machines and mobile van outlets in reaching hard-to-reach and high-risk groups of injecting drug users (IDUs): a review

    PubMed Central

    Islam, Md Mofizul; Conigrave, Katherine M

    2007-01-01

    Reaching hard-to-reach and high-risk injecting drug users (IDUs) is one of the most important challenges for contemporary needle syringe programs (NSPs). The aim of this review is to examine, based upon the available international experience, the effectiveness of syringe vending machines and mobile van/bus based NSPs in making services more accessible to these hard-to-reach and high-risk groups of IDUs. A literature search revealed 40 papers/reports, of which 18 were on dispensing machines (including vending and exchange machines) and 22 on mobile vans. The findings demonstrate that syringe dispensing machines and mobile vans are promising modalities of NSPs, which can make services more accessible to the target group and in particular to the harder-to-reach and higher-risk groups of IDUs. Their anonymous and confidential approaches make services attractive, accessible and acceptable to these groups. These two outlets were found to be complementary to each other and to other modes of NSPs. Services through dispensing machines and mobile vans in strategically important sites are crucial elements in continuing efforts in reducing the spread of HIV and other blood borne viruses among IDUs. PMID:17958894

  1. Assessing the role of syringe dispensing machines and mobile van outlets in reaching hard-to-reach and high-risk groups of injecting drug users (IDUs): a review.

    PubMed

    Islam, Md Mofizul; Conigrave, Katherine M

    2007-10-24

    Reaching hard-to-reach and high-risk injecting drug users (IDUs) is one of the most important challenges for contemporary needle syringe programs (NSPs). The aim of this review is to examine, based upon the available international experience, the effectiveness of syringe vending machines and mobile van/bus based NSPs in making services more accessible to these hard-to-reach and high-risk groups of IDUs. A literature search revealed 40 papers/reports, of which 18 were on dispensing machines (including vending and exchange machines) and 22 on mobile vans. The findings demonstrate that syringe dispensing machines and mobile vans are promising modalities of NSPs, which can make services more accessible to the target group and in particular to the harder-to-reach and higher-risk groups of IDUs. Their anonymous and confidential approaches make services attractive, accessible and acceptable to these groups. These two outlets were found to be complementary to each other and to other modes of NSPs. Services through dispensing machines and mobile vans in strategically important sites are crucial elements in continuing efforts in reducing the spread of HIV and other blood borne viruses among IDUs.

  2. A hypervelocity launcher for simulated large fragment space debris impacts at 10 km/s

    NASA Technical Reports Server (NTRS)

    Tullos, R. J.; Gray, W. M.; Mullin, S. A.; Cour-Palais, B. G.

    1989-01-01

    The background, design, and testing of two explosive launchers for simulating large fragment space debris impacts are presented. The objective was to develop a launcher capable of launching one gram aluminum fragments at velocities of 10 km/s. The two launchers developed are based on modified versions of an explosive shaped charge, common in many military weapons. One launcher design has yielded a stable fragment launch of approximately one gram of aluminum at 8.93 km/s velocity. The other design yielded velocities in excess of 10 km/s, but failed to produce a cohesive fragment launch. This work is ongoing, and future plans are given.

  3. Design and coupling characteristics of lower-hybrid launcher for TPX

    SciTech Connect

    Hubbard, A.E.; Porkolab, M. ); Bernabei, S.; Greenough, N. ); Goranson, P.; Swain, D.; Yugo, J. )

    1994-10-15

    The physics and mechanical design of the LHCD launcher for the proposed TPX experiment is presented. The main role of this system is current drive and current profile control, requiring a flexible and well defined spectrum. The launcher features 32 independently phasable guides in each of 4 rows. Coupling calculations indicate that low reflection coefficients can be achieved over the whole range of phasing by adjusting the launcher position. Good directivity is predicted over a wide range of densities. The mechanical design of the launcher is complicated by the high expected thermal loads and radiation fluxes. A design which incorporates these requirements is outlined.

  4. Design and coupling characteristics of lower-hybrid launcher for TPX

    NASA Astrophysics Data System (ADS)

    Hubbard, A. E.; Porkolab, M.; Bernabei, S.; Greenough, N.; Goranson, P.; Swain, D.; Yugo, J.

    1994-10-01

    The physics and mechanical design of the LHCD launcher for the proposed TPX experiment is presented. The main role of this system is current drive and current profile control, requiring a flexible and well defined spectrum. The launcher features 32 independently phasable guides in each of 4 rows. Coupling calculations indicate that low reflection coefficients can be achieved over the whole range of phasing by adjusting the launcher position. Good directivity is predicted over a wide range of densities. The mechanical design of the launcher is complicated by the high expected thermal loads and radiation fluxes. A design which incorporates these requirements is outlined.

  5. The Physics Performance Of The Front Steering Launcher For The ITER ECRH Upper Port

    SciTech Connect

    Henderson, M.; Chavan, R.; Nikkola, P.; Sanchez, F.; Sauter, O.; Shidara, H.; Ramponi, G.; Saibene, G.; Zohm, H.

    2005-09-26

    The capability of any given e.m.-wave plasma heating system to be utilized for physics applications depends strongly on the technical properties of the launching antenna (or launcher). An effective ECH launcher must project a small mm-wave beam spot size far into the plasma and 'steer' the beam across a large fraction of the plasma cross section (along the resonance surface). Thus the choice in the launcher concept and design may either severely limit or enhance the capability of a heating system to be effectively applied for physics applications, such as sawtooth stabilization, control of the Neoclassical Tearing Mode (NTM), Edge Localized Mode (ELM) control, etc. Presently, two antenna concepts are under consideration for the ITER upper port ECH launcher: front steering (FS) and remote steering (RS) launchers. The RS launcher has the technical advantage of easier maintenance access to the steering mirror, which is isolated from the torus vacuum. The FS launcher places the steering mirror near the plasma increasing the technical challenges, but significantly enhancing the focusing and steering capabilities of the launcher, offering a threefold increase in NTM stabilization efficiency over the RS launcher as well as the potential for application to other critical physics issues such as ELM or sawtooth control.

  6. Electromechanical Dynamics Simulations of Superconducting LSM Rocket Launcher System in Attractive-Mode

    NASA Technical Reports Server (NTRS)

    Yoshida, Kinjiro; Hayashi, Kengo; Takami, Hiroshi

    1996-01-01

    Further feasibility study on a superconducting linear synchronous motor (LSM) rocket launcher system is presented on the basis of dynamic simulations of electric power, efficiency and power factor as well as the ascending motions of the launcher and rocket. The advantages of attractive-mode operation are found from comparison with repulsive-mode operation. It is made clear that the LSM rocket launcher system, of which the long-stator is divided optimally into 60 sections according to launcher speeds, can obtain high efficiency and power factor.

  7. Design and performance of a multi-stage cylindrical reconnection launcher

    SciTech Connect

    Kaye, R.J.; Brawley, E.L.; Duggin, B.W.; Cnare, E.C.; Rovang, D.C.; Widner, M.M. )

    1991-01-01

    A multi-stage, cylindrical reconnection launcher is being tested to demonstrate electrically-contactless, induction-launch technology for solenoidal coil geometry. A 6-stage launcher system is being developed to accelerate a 5 kg mass from rest to 300 m/s with a stored energy of {ge}200 kJ per coil stage. This launcher will provide data fro model verification and the engineering basis for proceeding with larger multistage systems. This paper describes the design of the multi-stage, discrete-coil launcher. Integration of coils, projectile, power systems, and real-time fire control are discussed. Results of multi-stage firings are presented.

  8. Projectile transverse motion and stability in electromagnetic induction launchers

    SciTech Connect

    Shokair, I.R.

    1993-12-31

    The transverse motion of a projectile in an electromagnetic induction launcher is considered. The equations of motion for translation and rotation are derived assuming a rigid projectile and a flyway restoring force per unit length that is proportional to the local displacement. Linearized transverse forces and torques due to energized coils are derived for displaced or tilted armature elements based on a first order perturbation method. The resulting equations of motion for a rigid projectile composed of multiple elements in a multi-coil launcher are analyzed as a coupled oscillator system of equations and a simple linear stability condition is derived. The equations of motion are incorporated into the 2-D Slingshot circuit code and numerical solutions for the transverse motion are obtained. For a launcher with a 10 cm bore radius with a 40 cm long solid armature, we find that stability is achieved with a restoring force (per unit length) constant of k {approx} 1 {times} 10{sup 8} N/m{sup 2}. For k = 1.5 {times} 10{sup 8} N/m{sup 2} and sample coil misalignment modeled as a sine wave of 1 mm amplitude at wavelengths of one or two meters, the projectile displacement grows to a maximum of 4 mm. This growth is due to resonance between the natural frequency of the projectile transverse motion and the coil displacement wavelength. This resonance does not persist because of the changing axial velocity. Random coil displacement is also found to cause roughly the same projectile displacement. For the maximum displacement a rough estimate of the transverse pressure is 50 bars. Results for a wound armature with uniform current density throughout show very similar displacements.

  9. British government, industry agree to fund Hotel launcher studies

    NASA Astrophysics Data System (ADS)

    Brown, D. A.

    1986-02-01

    A program status assessment is presented for the horizontal takeoff and landing 'Hotol' single-stage-to-orbit space launcher, for which parallel, two-year airframe and propulsion system proof-of-concept studies have been approved. A two-year initial development program for the airframe would be followed by a four-year development and manufacturing phase that would begin upon the propulsion system concept's successful demonstration. Flight trials could begin in 1996. A number of significant modifications have already been made to the initial design concept, such as to the foreplanes, afterbody, engine intake, and orbital control system.

  10. A high energy launcher for Trans Atmospheric Vehicles

    NASA Astrophysics Data System (ADS)

    Lantz, Edward

    1987-12-01

    For maximum efficiency Trans Atmospheric Vehicles (TAV's) must have high specific impulse (Isp) propulsion for takeoff and for accelerating after takeoff. This is when the TAV is the heaviest and consequently when the drag and the loss rate of energy to earth's gravity is the greatest. A ground-based horizontal launcher provides a very high effective Isp, and if properly designed, can launch TAV's at ramjet operating speed. It is found that for the acceleration to Mach 5 the average Isp for hydrogen fueled ramjet engines is higher than that for air turbo rocket engines.

  11. Inhibited Shaped Charge Launcher Testing of Spacecraft Shield Designs

    NASA Technical Reports Server (NTRS)

    Grosch, Donald J.

    1996-01-01

    This report describes a test program in which several orbital debris shield designs were impact tested using the inhibited shaped charge launcher facility at Southwest Research Institute. This facility enables researchers to study the impact of one-gram aluminum projectiles on various shielding designs at velocities above 11 km/s. A total of twenty tests were conducted on targets provided by NASA-MSFC. This report discusses in detail the shield design, the projectile parameters and the test configuration used for each test. A brief discussion of the target damage is provided, as the detailed analysis of the target response will be done by NASA-MSFC.

  12. Inhibited Shaped Charge Launcher Testing of Spacecraft Shield Designs

    NASA Technical Reports Server (NTRS)

    Grosch, Donald J.

    1996-01-01

    This report describes a test program in which several orbital debris shield designs were impact tested using the inhibited shaped charge launcher facility at Southwest Research Institute. This facility enables researchers to study the impact of one-gram aluminum projectiles on various shielding designs at velocities above 11 km/s. A total of twenty tests were conducted on targets provided by NASA-MSFC. This report discusses in detail the shield design, the projectile parameters and the test configuration used for each test. A brief discussion of the target damage is provided, as the detailed analysis of the target response will be done by NASA-MSFC.

  13. The Skylark sounding rocket program and future launcher developments by British Aerospace (Space Systems) Ltd.

    NASA Astrophysics Data System (ADS)

    Ellis, J. A.

    1989-06-01

    The past history of the Skylark sounding rocket, is reported. A background to the rationalization of the variations of rocket now available, is provided. The last two years launch program, with a summary of future scheduled programs, is listed. The future interests of British Aerospace in rocket launchers, in particular LittLEO (the small launcher for payloads into low earth orbit), are described.

  14. Design Performance of Front Steering-Type Electron Cyclotron Launcher for ITER

    SciTech Connect

    Takahashi, K.; Imai, T.; Kobayashi, N.; Sakamoto, K.; Kasugai, A.; Hayakawa, A.; Mori, S.; Mohri, K.

    2005-01-15

    The performance of a front steering (FS)-type electron cyclotron launcher designed for the International Thermonuclear Experimental Reactor (ITER) is evaluated with a thermal, electromagnetic, and nuclear analysis of the components; a mechanical test of a spiral tube for the steering mirror; and a rotational test of bearings. The launcher consists of a front shield and a launcher plug where three movable optic mirrors to steer incident multimegawatt radio-frequency beam power, waveguide components, nuclear shields, and vacuum windows are installed. The windows are located behind a closure plate to isolate the transmission lines from the radioactivated circumstance (vacuum vessel). The waveguide lines of the launcher are doglegged to reduce the direct neutron streaming toward the vacuum windows and other components. The maximum stresses on the critical components such as the steering mirror, its cooling tube, and the front shield are less than their allowable stresses. It was also identified that the stress on the launcher, which yielded from electromagnetic force caused by plasma disruption, was a little larger than the criteria, and a modification of the launcher plug structure was necessary. The nuclear analysis result shows that the neutron shield capability of the launcher satisfies the shield criteria of the ITER. It concludes that the design of the FS launcher is generally suitable for application to the ITER.

  15. 10. 22'X34' original blueprint, VariableAngle Launcher, 'SIDE VIEW CAMERA CARSTEEL ...

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

    10. 22'X34' original blueprint, Variable-Angle Launcher, 'SIDE VIEW CAMERA CAR-STEEL FRAME AND AXLES' drawn at 1/2'=1'-0'. (BOURD Sketch # 209124). - Variable Angle Launcher Complex, Camera Car & Track, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  16. 13. 22'X34' original vellum, VariableAngle Launcher, 'SIDEVIEW CAMERA CAR TRACK ...

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

    13. 22'X34' original vellum, Variable-Angle Launcher, 'SIDEVIEW CAMERA CAR TRACK DETAILS' drawn at 1/4'=1'-0' (BUORD Sketch # 208078, PAPW 908). - Variable Angle Launcher Complex, Camera Car & Track, CA State Highway 39 at Morris Reservior, Azusa, Los Angeles County, CA

  17. Studies to reduce material erosion in electrothermal launchers

    SciTech Connect

    Gilligan, J.; Bourham, M.; Hankins, O.; Auciello, O.; Tallavarjula, S.; Mobanti, R. . Dept. of Nuclear Engineering)

    1991-01-01

    This paper reports that during the exposure of launcher components of high heat fluxes a vapor shield (plasma boundary layer) is formed which absorbs a fraction of the incoming energy, and thus naturally reduces the surface erosion. Computer simulation has shown that a strong externally applied magnetic field parallel to the surface may reduce the surface erosion, since the energy transport though the vapor shield will be reduced due to decreased turbulence. The experimental electrothermal launcher device SIRENS has been operated to measure the erosion of material surfaces subjected to high heat flux from a high density low temperature plasma (1-3 eV) with a strong applied magnetic field. The plasma is produced by the ablation of the insulator (Lexan), with currents up to 100 kA over a pulse length of 100{mu}s, and flows through a cylindrical barrel which serves as the material sample. Ablation and erosion for both the insulator and sample surfaces are caused by convection and radiation emitted from the plasma. The ablated thickness of the Lexan insulator compares favorably with predicted values. The key parameter is f, the fraction of total incident energy that is transmitted to the eroding surface which is flux and material dependent but in the range 5-20%.

  18. Methodologies for launcher-payload coupled dynamic analysis

    NASA Astrophysics Data System (ADS)

    Fransen, S. H. J. A.

    2012-06-01

    An important step in the design and verification process of spacecraft structures is the coupled dynamic analysis with the launch vehicle in the low-frequency domain, also referred to as coupled loads analysis (CLA). The objective of such analyses is the computation of the dynamic environment of the spacecraft (payload) in terms of interface accelerations, interface forces, center of gravity (CoG) accelerations as well as the internal state of stress. In order to perform an efficient, fast and accurate launcher-payload coupled dynamic analysis, various methodologies have been applied and developed. The methods are related to substructuring techniques, data recovery techniques, the effects of prestress and fluids and time integration problems. The aim of this paper was to give an overview of these methodologies and to show why, how and where these techniques can be used in the process of launcher-payload coupled dynamic analysis. In addition, it will be shown how these methodologies fit together in a library of procedures which can be used with the MSC.Nastran™ solution sequences.

  19. Comparative study of component erosion for electromagnetic and electrothermal launchers

    NASA Astrophysics Data System (ADS)

    Bourham, M. A.; Hankins, O. E.; Gilligan, J. G.; Hurley, J. D.; Earnhart, J. R.

    1993-01-01

    The electrothermal launcher SIRENS has been used to study the erosion of critical components (rails and insulators) of plasma-driven launchers. SIRENS can produce high-density (above 10 exp 25/cu m) low-temperature (1-3 eV) plasma, formed by the ablation of the insulator (Lexan), with currents up to 100 kA. The incident heat flux varies between 2 to 90 GW/sq m over 100 microsec duration, for input energies 1-10 kJ. Erosion studies have been performed on several insulators, pure and coated metals, alloys and several graphite grades. The fraction of the total incident energy that is transmitted to the eroded surface varies from 12 to 30 percent for the materials tested and decreases to 5-7 percent as the incident energy fluence increases. Such reduction in erosion for a given incident fluence is due to the vapor shield effect. The scaling law for the energy transmission factor through the vapor shield layer was obtained for the exposed materials.

  20. Chunk projectile launch using the Sandia Hypervelocity Launcher Facility

    SciTech Connect

    Chhabildas, L.C.; Trucano, T.G.; Reinhart, W.D.; Hall, C.A.

    1994-07-01

    An experimental technique is described to launch an intact ``chunk,`` i.e. a 0.3 cm thick by 0.6 cm diameter cylindrical titanium alloy (Ti-6Al-4V) flyer, to 10.2 km/s. The ability to launch fragments having such an aspect ratio is important for hypervelocity impact phenomenology studies. The experimental techniques used to accomplish this launch were similar but not identical to techniques developed for the Sandia HyperVelocity Launcher (HVL). A confined barrel impact is crucial in preventing the two-dimensional effects from dominating the loading response of the projectile chunk. The length to diameter ratio of the metallic chunk that is launched to 10.2 km/s is 0.5 and is an order of magnitude larger than those accomplished using the conventional hypervelocity launcher. The multi-dimensional, finite-difference (finite-volume), hydrodynamic code CTH was used to evaluate and assess the acceleration characteristics i.e., the in-bore ballistics of the chunky projectile launch. A critical analysis of the CTH calculational results led to the final design and the experimental conditions that were used in this study. However, the predicted velocity of the projectile chunk based on CTH calculations was {approximately} 6% lower than the measured velocity of {approximately}10.2 km/S.

  1. Numerical predictions of EML (electromagnetic launcher) system performance

    SciTech Connect

    Schnurr, N.M.; Kerrisk, J.F.; Davidson, R.F.

    1987-01-01

    The performance of an electromagnetic launcher (EML) depends on a large number of parameters, including the characteristics of the power supply, rail geometry, rail and insulator material properties, injection velocity, and projectile mass. EML system performance is frequently limited by structural or thermal effects in the launcher (railgun). A series of computer codes has been developed at the Los Alamos National Laboratory to predict EML system performance and to determine the structural and thermal constraints on barrel design. These codes include FLD, a two-dimensional electrostatic code used to calculate the high-frequency inductance gradient and surface current density distribution for the rails; TOPAZRG, a two-dimensional finite-element code that simultaneously analyzes thermal and electromagnetic diffusion in the rails; and LARGE, a code that predicts the performance of the entire EML system. Trhe NIKE2D code, developed at the Lawrence Livermore National Laboratory, is used to perform structural analyses of the rails. These codes have been instrumental in the design of the Lethality Test System (LTS) at Los Alamos, which has an ultimate goal of accelerating a 30-g projectile to a velocity of 15 km/s. The capabilities of the individual codes and the coupling of these codes to perform a comprehensive analysis is discussed in relation to the LTS design. Numerical predictions are compared with experimental data and presented for the LTS prototype tests.

  2. Variational Dynamic Coupled-Loads Analysis within the Frame of Launcher Upper Stage Development

    NASA Astrophysics Data System (ADS)

    Meitzner, R.; Abdoly, K.; Beuchel, W.; Stellino, W.

    2014-06-01

    During development the definition of realistic mechanical loads is a major challenge and milestone for space launcher programs. Especially the definition of dynamic loads for large structures, e.g. cryogenic tanks, and equipments, based on multi-variational payload configurations is a key element in the frame of new launcher upper stage developments.This paper presents a methodology to define realistic dynamic loads based on multi-variational dynamic coupled- loads analyses in the global launcher system up to equipment level.The complex challenge towards this task is to perform about 256000 complete coupled-loads analyses for the entire launcher upper stage including various recovery items within two weeks.The shown example describes multi-variational dynamic coupled-loads analyses and their post processing for the complete Ariane 5 Midlife Evolution launcher including the new upper stage using Nastran and PUMA3D software.

  3. Characterization of the supersonic wake of a generic space launcher

    NASA Astrophysics Data System (ADS)

    Schreyer, A.-M.; Stephan, S.; Radespiel, R.

    2017-03-01

    The wake flow of a generic axisymmetric space-launcher model is investigated experimentally for flow cases with and without propulsive jet to gain insight into the wake-flow phenomena at a supersonic stage of the flight trajectory which is especially critical with respect to dynamic loads on the structure. Measurements are performed at Mach 2.9 and a Reynolds number Re D = 1.3 × 106 based on model diameter D. The nozzle exit velocity of the jet is at Mach 2.5, and the flow is moderately underexpanded ( p e/ p ∞ = 5.7). The flow topology is described based on velocity measurements in the wake by means of particle image velocimetry and schlieren visualizations. Mean and fluctuating mass-flux profiles are obtained from hot-wire measurements, and unsteady wall-pressure measurements on the main-body base are performed simultaneously. This way, the evolution of the wake flow and its spectral content can be observed along with the footprint of this highly dynamic flow on the launcher main-body base. For the case without propulsive jet, a large separated zone is forming downstream of the main body shoulder, and the flow is reattaching further downstream on the afterbody. The afterexpanding propulsive jet (air) causes a displacement of the shear layer away from the wall, preventing the reattachment of the flow. In the spectral analysis of the baseline case, a dominant frequency around St D = 0.25 is found in the pressure-fluctuation signal at the main-body base of the launcher. This frequency is related to the shedding of the separation bubble and is less pronounced in the presence of the propulsive jet. In the shear layer itself, the spectra obtained from the hot-wire signal have a more broadband low-frequency content, which also reflects the characteristic frequency of turbulent structures convected in the shear layer, a swinging motion ( St D = 0.6), as well as the radial flapping motion of the shear layer ( St D = 0.85), respectively. Moving downstream along the

  4. Plasma-material interaction in electrothermal and electromagnetic launchers

    NASA Astrophysics Data System (ADS)

    Bourham, M. A.; Gilligan, J. G.; Hankins, O. E.

    1993-07-01

    Various material surfaces have been exposed to high heat fluxes from 2 to 80 GW/sq m over 100 microsec duration using the electrothermal launcher, SIRENS. The vapor shield is effective in reducing the heat to the ablating surface, and the energy transmission factor through the vapor shield decreases as the incident heat flux increases. Results show good agreement with code predictions. Visible light emission spectra have been observed both in-bore and from the muzzle flash of the barrel, and from the flash of the source. Measurements of visible emission from the source indicate time averaged temperatures of 1 to 3 eV, and about 1 to 2 eV along the axis of the device, which agree with the theory and experimental measurements of the average heat flux and plasma conductivity.

  5. Impact of Launchers on the Environment in French Guiana

    NASA Astrophysics Data System (ADS)

    Richard, S.; Chemoul, B.

    2012-01-01

    The main combustion products of the Ariane 5 solid rocket boosters are alumina and chlorhyde gas. When the launcher lift off the significant concentrations of this components are around the launch zone. We use samplers to evaluate the concentrations of this two elements. To optimize the localisation of the samplers we use a model to obtain the projected traces of the combustion cloud according to meteorological data (software sarrim). During the first seconds of takes 1000 m3 of water flood the base right to decrease the acoustic vibration. The major parts of the pollutants fall close to the launch zone and acidic cloud is formed. Once having stabilized the cloud begins diluting, it is subjected to the influence of the different layers of wind. To measure air quality we use first continuous analysers, secondly containers with distilled water to sample the acidic particles from the cloud. We also monitor the physicochemical quality of water in a river near the launch zone, the impact of the combustion products on vegetation, the aquatic fauna. Noise and vibrations are also measured. For terrestrial fauna like birds, we monitor the general population and a colony of wade. The most important colony of this species is located on the base : around 75% of the population of the French Guiana. We use also a new protocol to estimate the impact of launch by measuring the thickness of eggshells. We use research results which show that calcium can be replaced by alumina. When the thickness of eggshells is thin, the reproduction can be affected. For each measurement campaign, we have more than 100 sites and around 600 samples. The results shows that the land around the space centre is like a natural refuge. The impact of the launches is low, hunting is forbidden and security personal controls the zone base is a protected zone. The space centre is now a natural wildlife refuge. For the two new launchers, Vega and Soyuz, we will also monitor the environmental impact of the launch

  6. Reconnection launcher projectile heating using the modified REGGIE code

    SciTech Connect

    Freemen, J.R.

    1989-01-01

    Modified REGGIE is a variant of the REGGIE reconnection launcher code. It was written to provide a more economical tool for studying multi-stage projectile heating. The validity of the approximations made in modified REGGIE was determined by comparisons with both full REGGIE and WARP-10 computations. Modified REGGIE runs about seven times faster than full REGGIE. Modified REGGIE was used to study projectile heating for a specific force profile proposed by M. Cowan. The total energy dissipated after seven stages was reduced by a factor of about eight compared to the present day conventional discrete coil system. This reduction would allow higher peak velocities to be achieved prior to ablation. 5 refs., 4 figs., 3 tabs.

  7. Effect of the electric field pattern on the generation of fast electrons in front of lower hybrid launchers

    NASA Astrophysics Data System (ADS)

    Valade, Laurent; Fuchs, Vladimir; Ekedahl, Annika; Petrzilka, Vaclav; Colas, Laurent; Goniche, Marc; Hillairet, Julien; Li, Miaohui; Zhang, Bin

    2015-12-01

    The effect of the detailed waveguide spectrum on the electron acceleration has been studied for the 3.7 GHz LHCD launchers in Tore Supra, i.e. the ITER-like passive-active multijunction (PAM) launcher and the fully-active-multijunction (FAM) launcher, using test electron modelling technique. The detailed launched antenna wave spectrum is used as input to the code that computes the dynamics of the electrons in the electric field. Comparison with the LHCD launchers in EAST, operating at 2.45 GHz and 4.6 GHz, has also been made. The simulations show that the PAM-design generates lower flux of fast electrons than FAM-launchers, this could be the consequence of the wider waveguide of PAM-launcher (14.65 mm for Tore-Supra) than FAM-launcher (8 mm for Tore-Supra).

  8. Effect of the electric field pattern on the generation of fast electrons in front of lower hybrid launchers

    SciTech Connect

    Valade, Laurent Ekedahl, Annika; Colas, Laurent; Goniche, Marc; Hillairet, Julien; Fuchs, Vladimir; Petrzilka, Vaclav; Li, Miaohui; Zhang, Bin

    2015-12-10

    The effect of the detailed waveguide spectrum on the electron acceleration has been studied for the 3.7 GHz LHCD launchers in Tore Supra, i.e. the ITER-like passive-active multijunction (PAM) launcher and the fully-active-multijunction (FAM) launcher, using test electron modelling technique. The detailed launched antenna wave spectrum is used as input to the code that computes the dynamics of the electrons in the electric field. Comparison with the LHCD launchers in EAST, operating at 2.45 GHz and 4.6 GHz, has also been made. The simulations show that the PAM-design generates lower flux of fast electrons than FAM-launchers, this could be the consequence of the wider waveguide of PAM-launcher (14.65 mm for Tore-Supra) than FAM-launcher (8 mm for Tore-Supra)

  9. The road to the Next-Generation European Launcher - an overview of the FLPP

    NASA Astrophysics Data System (ADS)

    Ackermann, Jürgen; Breteau, Jérôme; Kauffmann, Jens; Ramusat, Guy; Tumino, Giorgio

    2005-08-01

    The Future Launchers Preparatory Programme (FLPP) was approved by the last ESA Ministerial Council and began in February 2004, ending a long period without a programme dedicated to future launchers at the European level. The aim is to prepare the Next Generation Launcher to be operational around 2020. System studies and technology activities therefore need to be conducted, including ground and in-flight tests, to foster new technologies capable of providing high performance and reliability, together with low life-cycle costs. The final choice between an expendable or reusable type of launch vehicle will be made on the basis of proven technological readiness and consolidated cost and risk assessments.

  10. I've got a mobile phone too! Hard and soft assistive technology customization and supportive call centres for people with disability.

    PubMed

    Darcy, Simon; Green, Jenny; Maxwell, Hazel

    2017-05-01

    The purpose of this article is to examine the use of a mobile technology platform, software customization and technical support services by people with disability. The disability experience is framed through the participants' use of the technology, their social participation. A qualitative and interpretive research design was employed using a three-stage process of observation and semi-structured interviews of people with disability, a significant other and their service provider. Transcripts were analyzed to examine the research questions through the theoretical framework of PHAATE - Policy, Human, Activity, Assistance and Technology and Environment. The analysis revealed three emergent themes: 1. Engagement and activity; 2. Training, support and customization; and 3. Enablers, barriers and attitudes. The findings indicate that for the majority of users, the mobile technology increased the participants' communication and social participation. However, this was not true for all members of the pilot with variations due to disability type, support needs and availability of support services. Most participants, significant others and service providers identified improvements in confidence, security, safety and independence of those involved. Yet, the actions and attitudes of some of the significant others and service providers acted as a constraint to the adoption of the technology. Implications for Rehabilitation Customized mobile technology can operate as assistive technology providing a distinct benefit in terms of promoting disability citizenship. Mobile technology used in conjunction with a supportive call centre can lead to improvements in confidence, safety and independence for people experiencing disability. Training and support are critical in increasing independent use of mobile technology for people with disability. The enjoyment, development of skills and empowerment gained through the use of mobile technology facilitate the social inclusion of people with

  11. "It Is Hard to Stay in England": Itineraries, Routes, and Dead Ends--An (Im)mobility Study of Nurses Who Became Carers

    ERIC Educational Resources Information Center

    Cuban, Sondra

    2010-01-01

    This article presents findings from an Economic Social Research Council (ESRC) study on the roles of education in the trajectories of health care professionals who migrated to England and became carers. The study looks at the downward mobility and deskilling of these women, and their struggles to reverse their bungled career paths. The author maps…

  12. KENNEDY SPACE CENTER, FLA. - Framed between palm trees, solid rocket boosters loom above the Mobile Launcher Platform (MLP) as the crawler transporter slowly moves it along the crawlerway. The journey is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - Framed between palm trees, solid rocket boosters loom above the Mobile Launcher Platform (MLP) as the crawler transporter slowly moves it along the crawlerway. The journey is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  13. KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  14. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The view reveals the river gravel surface that is 4 inches thick on the straightaway sections and 8 inches thick on curves. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The view reveals the river gravel surface that is 4 inches thick on the straightaway sections and 8 inches thick on curves. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  15. KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  16. KENNEDY SPACE CENTER, FLA. - Carrying a set of twin solid rocket boosters, the crawler transporter slowly moves the Mobile Launcher Platform (MLP) past the NASA-KSC News Center where the U.S. flag flies daily. The journey is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - Carrying a set of twin solid rocket boosters, the crawler transporter slowly moves the Mobile Launcher Platform (MLP) past the NASA-KSC News Center where the U.S. flag flies daily. The journey is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  17. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (on the horizon at right; Pad 39B is at far left), and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (on the horizon at right; Pad 39B is at far left), and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  18. KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician walks towards the intersection of the crawlerway beside a crawler-transporter moving Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician walks towards the intersection of the crawlerway beside a crawler-transporter moving Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  19. KENNEDY SPACE CENTER, FLA. - As the crawler transporter slowly moves the Mobile Launcher Platform (MLP) out of the Vehicle Assembly Building, the two solid rocket boosters on top are framed in the doorway. The move is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - As the crawler transporter slowly moves the Mobile Launcher Platform (MLP) out of the Vehicle Assembly Building, the two solid rocket boosters on top are framed in the doorway. The move is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  20. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (framed between the boosters), and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (framed between the boosters), and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  1. KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, along the crawlerway in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, along the crawlerway in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  2. KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician inspects the shoes on one of eight tracks of a crawler-transporter (CT). The CT is moving Mobile Launcher Platform (MLP) number 3 with a set of twin solid rocket boosters bolted on top to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician inspects the shoes on one of eight tracks of a crawler-transporter (CT). The CT is moving Mobile Launcher Platform (MLP) number 3 with a set of twin solid rocket boosters bolted on top to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  3. KENNEDY SPACE CENTER, FLA. - The crawler transporter has slowly moved the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - The crawler transporter has slowly moved the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  4. KENNEDY SPACE CENTER, FLA. - Seen across the water of the Launch Complex 39 turn basin, a crawler-transporter, carrying Mobile Launcher Platform (MLP) number 3 with a set of twin solid rocket boosters bolted atop, crawls out of the 525-foot-tall Vehicle Assembly Building during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Seen across the water of the Launch Complex 39 turn basin, a crawler-transporter, carrying Mobile Launcher Platform (MLP) number 3 with a set of twin solid rocket boosters bolted atop, crawls out of the 525-foot-tall Vehicle Assembly Building during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  5. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, crawl out of the Vehicle Assembly Building (VAB) in support of the second engineering analysis vibration test on the crawler and MLP. In the background is another MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, crawl out of the Vehicle Assembly Building (VAB) in support of the second engineering analysis vibration test on the crawler and MLP. In the background is another MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  6. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (on the horizon) and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (on the horizon) and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  7. KENNEDY SPACE CENTER, FLA. - A high-flying bird takes a closer look at the Mobile Launcher Platform (MLP) number 3 with twin solid rocket boosters bolted to it as it crawls toward Launch Pad 39A, in the background. The crawler is moving along the crawlerway at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - A high-flying bird takes a closer look at the Mobile Launcher Platform (MLP) number 3 with twin solid rocket boosters bolted to it as it crawls toward Launch Pad 39A, in the background. The crawler is moving along the crawlerway at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  8. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, crawls away from the Vehicle Assembly Building in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, crawls away from the Vehicle Assembly Building in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  9. KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. In the distance, at left, is Launch Pad 39A. The water on the right of the crawlerway is the Banana River. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. In the distance, at left, is Launch Pad 39A. The water on the right of the crawlerway is the Banana River. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  10. KENNEDY SPACE CENTER, FLA. - As the crawler transporter slowly moves the Mobile Launcher Platform (MLP) out of the Vehicle Assembly Building, the driver of the front control cab can be seen. The MLP is carrying two solid rocket boosters for engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - As the crawler transporter slowly moves the Mobile Launcher Platform (MLP) out of the Vehicle Assembly Building, the driver of the front control cab can be seen. The MLP is carrying two solid rocket boosters for engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  11. KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, along the crawlerway in support of engineering analysis vibration tests on the crawler and MLP. In the distance, at left, is Launch Pad 39A. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, along the crawlerway in support of engineering analysis vibration tests on the crawler and MLP. In the distance, at left, is Launch Pad 39A. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  12. KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. On either side of the boosters on the horizon can be seen the two launch pads. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. On either side of the boosters on the horizon can be seen the two launch pads. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  13. KENNEDY SPACE CENTER, FLA. - Viewed across the turn basin in the Launch Complex 39 Area, the crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB). The journey is in support of engineering analysis vibration tests on the crawler and MLP. The water on the right of the crawlerway is the Banana River. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - Viewed across the turn basin in the Launch Complex 39 Area, the crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB). The journey is in support of engineering analysis vibration tests on the crawler and MLP. The water on the right of the crawlerway is the Banana River. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  14. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters bolted to it, atop the crawler-transporter, crawl to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. In the background are Launch Pads 39A (right) and 39B (left). The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters bolted to it, atop the crawler-transporter, crawl to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. In the background are Launch Pads 39A (right) and 39B (left). The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  15. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters bolted to it, atop the crawler-transporter, inches along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The MLP is viewed from the KSC News Center across the turn basin. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters bolted to it, atop the crawler-transporter, inches along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The MLP is viewed from the KSC News Center across the turn basin. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  16. KENNEDY SPACE CENTER, FLA. - The crawler transporter is slowly moving the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-17

    KENNEDY SPACE CENTER, FLA. - The crawler transporter is slowly moving the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  17. KENNEDY SPACE CENTER, FLA. - The crawler-transporter carrying Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, crawls to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. From this perspective, the Launch Control Center (left) and the 525-foot-tall Vehicle Assembly Building (right) in the background appear dwarfed by the 184-foot-tall boosters. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - The crawler-transporter carrying Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, crawls to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. From this perspective, the Launch Control Center (left) and the 525-foot-tall Vehicle Assembly Building (right) in the background appear dwarfed by the 184-foot-tall boosters. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  18. KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch away from the Vehicle Assembly Building (VAB) in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch away from the Vehicle Assembly Building (VAB) in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  19. KENNEDY SPACE CENTER, FLA. - A crawler-transporter carrying Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, crawls to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. From this perspective, the Launch Control Center (left) and the 525-foot-tall Vehicle Assembly Building (right) in the background appear dwarfed by the 184-foot-tall boosters. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - A crawler-transporter carrying Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, crawls to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. From this perspective, the Launch Control Center (left) and the 525-foot-tall Vehicle Assembly Building (right) in the background appear dwarfed by the 184-foot-tall boosters. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  20. KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician monitors the performance of a crawler-transporter as it moves Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, to the intersection in the crawlerway during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

    NASA Image and Video Library

    2003-11-21

    KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician monitors the performance of a crawler-transporter as it moves Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, to the intersection in the crawlerway during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

  1. KENNEDY SPACE CENTER, FLA. - Robert T. Nelson of KSC Security points to an approximately 24-foot-long crack on the Mobile Launcher Platform (MLP), which is holding the Space Shuttle Discovery en route to Launch Pad 39A for the STS-82 mission. Nelson was riding on the MLP when he heard a loud noise and noticed the crack. Rollout had begun shortly after 7 a.m. EST and was stopped at about 8:25 a.m. This Y-shaped crack is on the MLP surface and runs from near the left-hand solid rocket booster flame hole toward the near corner of the MLP. Rollout of Discovery resumed just past noon after structural engineers determined that the integrity of the MLP had not been compromised. Discovery is scheduled to lift off on the second Hubble Space Telescope servicing mission on Feb. 11.

    NASA Image and Video Library

    1997-01-17

    KENNEDY SPACE CENTER, FLA. - Robert T. Nelson of KSC Security points to an approximately 24-foot-long crack on the Mobile Launcher Platform (MLP), which is holding the Space Shuttle Discovery en route to Launch Pad 39A for the STS-82 mission. Nelson was riding on the MLP when he heard a loud noise and noticed the crack. Rollout had begun shortly after 7 a.m. EST and was stopped at about 8:25 a.m. This Y-shaped crack is on the MLP surface and runs from near the left-hand solid rocket booster flame hole toward the near corner of the MLP. Rollout of Discovery resumed just past noon after structural engineers determined that the integrity of the MLP had not been compromised. Discovery is scheduled to lift off on the second Hubble Space Telescope servicing mission on Feb. 11.

  2. KENNEDY SPACE CENTER, FLA. -Crawler-transporter (CT) number 2, moves away from the Vehicle Assembly Building, with a Mobile Launcher Platform on top, on a test run to the launch pad. The CT recently underwent modifications to the cab. The CT moves Space Shuttle vehicles between the VAB and launch pad. Moving on four double-tracked crawlers, the CT uses a laser guidance system and a leveling system for the journey that keeps the top of a Space Shuttle vertical within plus- or minus-10 minutes of arc. The system enables the CT-MLP-Shuttle to negotiate the ramp leading to the launch pads and keep the load level. Unloaded, the CT weighs 6 million pounds.

    NASA Image and Video Library

    2003-08-18

    KENNEDY SPACE CENTER, FLA. -Crawler-transporter (CT) number 2, moves away from the Vehicle Assembly Building, with a Mobile Launcher Platform on top, on a test run to the launch pad. The CT recently underwent modifications to the cab. The CT moves Space Shuttle vehicles between the VAB and launch pad. Moving on four double-tracked crawlers, the CT uses a laser guidance system and a leveling system for the journey that keeps the top of a Space Shuttle vertical within plus- or minus-10 minutes of arc. The system enables the CT-MLP-Shuttle to negotiate the ramp leading to the launch pads and keep the load level. Unloaded, the CT weighs 6 million pounds.

  3. KENNEDY SPACE CENTER, FLA. - Crawler-transporter (CT) number 2 nears the launch pad with a Mobile Launcher Platform (MLP) on top. After recent modifications to the cab and muffler system, the CT was taken on a test run. The CT moves Space Shuttle vehicles, situated on the MLP, between the VAB and launch pad. Moving on four double-tracked crawlers, the CT uses a laser guidance system and a leveling system for the journey that keeps the top of a Space Shuttle vertical within plus- or minus-10 minutes of arc. The system enables the CT-MLP-Shuttle to negotiate the ramp leading to the launch pads and keep the load level. Unloaded, the CT weighs 6 million pounds. Seen on top of the MLP are two tail service masts that support the fluid, gas and electrical requirements of the orbiter’s liquid oxygen and liquid hydrogen aft umbilicals.

    NASA Image and Video Library

    2003-08-19

    KENNEDY SPACE CENTER, FLA. - Crawler-transporter (CT) number 2 nears the launch pad with a Mobile Launcher Platform (MLP) on top. After recent modifications to the cab and muffler system, the CT was taken on a test run. The CT moves Space Shuttle vehicles, situated on the MLP, between the VAB and launch pad. Moving on four double-tracked crawlers, the CT uses a laser guidance system and a leveling system for the journey that keeps the top of a Space Shuttle vertical within plus- or minus-10 minutes of arc. The system enables the CT-MLP-Shuttle to negotiate the ramp leading to the launch pads and keep the load level. Unloaded, the CT weighs 6 million pounds. Seen on top of the MLP are two tail service masts that support the fluid, gas and electrical requirements of the orbiter’s liquid oxygen and liquid hydrogen aft umbilicals.

  4. KENNEDY SPACE CENTER, FLA. - Crawler-transporter (CT) number 2, moves away from the Vehicle Assembly Building with a Mobile Launcher Platform (MLP) on top on a test run to the launch pad. The CT recently underwent modifications to the cab. The CT moves Space Shuttle vehicles, situated on the MLP, between the VAB and launch pad. Moving on four double-tracked crawlers, the CT uses a laser guidance system and a leveling system for the journey that keeps the top of a Space Shuttle vertical within plus- or minus-10 minutes of arc. The system enables the CT-MLP-Shuttle to negotiate the ramp leading to the launch pads and keep the load level. Unloaded, the CT weighs 6 million pounds. Seen on top of the MLP are two tail service masts that support the fluid, gas and electrical requirements of the orbiter’s liquid oxygen and liquid hydrogen aft umbilicals.

    NASA Image and Video Library

    2003-08-18

    KENNEDY SPACE CENTER, FLA. - Crawler-transporter (CT) number 2, moves away from the Vehicle Assembly Building with a Mobile Launcher Platform (MLP) on top on a test run to the launch pad. The CT recently underwent modifications to the cab. The CT moves Space Shuttle vehicles, situated on the MLP, between the VAB and launch pad. Moving on four double-tracked crawlers, the CT uses a laser guidance system and a leveling system for the journey that keeps the top of a Space Shuttle vertical within plus- or minus-10 minutes of arc. The system enables the CT-MLP-Shuttle to negotiate the ramp leading to the launch pads and keep the load level. Unloaded, the CT weighs 6 million pounds. Seen on top of the MLP are two tail service masts that support the fluid, gas and electrical requirements of the orbiter’s liquid oxygen and liquid hydrogen aft umbilicals.

  5. Electromagnetic loads on ion cyclotron and lower hybrid launchers for TPX

    SciTech Connect

    Yugo, J.J.; Fogelman, C.H.; Goranson, P.L.; Conner, D.L.; Swain, D.W.; Sayer, R.O.

    1995-12-31

    The ion cyclotron (IC) and lower hybrid (LH) launchers for the Tokamak Physics Experiment (TPX) will be subjected to significant forces resulting from eddy currents induced in the launchers from the rapid decay of the plasma current during plasma disruption events. The launchers are being designed to withstand the forces resulting from a peak plasma current decay rate of 1.2 MA/ms and an average current decay rate of 0.5 MA/ms from an initial plasma current of 2 MA. The desire for highly reliable and low cost fabrication techniques prompted the comparison of pure copper and dispersion-hardened copper for the LH launcher. Its low nuclear activation rate, high electrical resistance, and high strength motivated the evaluation of Titanium as an IC antenna material.

  6. Microwave impedance matching strategies of an applicator supplied by a bi-directional magnetron waveguide launcher.

    PubMed

    Roussy, Georges; Kongmark, Nils

    2003-01-01

    It is shown that a bi-directional waveguide launcher can be used advantageously for reducing the reflection coefficient mismatch of an input impedance of an applicator. In a simple bi-directional waveguide launcher, the magnetron is placed in the waveguide and generates a nominal field distribution with significant output impedance in both directions of the waveguide. If a standing wave is tolerated in the torus, which connects the launcher and the applicator, the power transfer from the magnetron to the applicator can be optimal, without using special matching devices. It is also possible to match the bi-directional launcher with two inductance stubs near the antenna of the magnetron and use them for supplying a two-input applicator without reflection.

  7. Design and performance of a multi-stage cylindrical reconnection launcher

    SciTech Connect

    Kaye, R.J.; Duggin, B.W.; Cnare, E.C.; Rovang, D.C.; Widner, M.M. ); Brawley, E.L. )

    1989-01-01

    A multi-stage, cylindrical, reconnection launcher is being tested to demonstrate electrically-contactless, induction-launch technology for solenoidal coil geometry. A 6-stage launcher system is being developed to accelerate a 5 kg mass from rest to 300 m/s with a stored energy of {ge}200 kJ per coil stage. This launcher will provide data for model verification and the engineering basis for proceeding with larger multistage systems. This paper describes the design of the multi-stage, discrete-coil launcher. Integration of coils, projectile, power systems, and real-time fire control are discussed. Results of multi-stage firings are presented. 6 refs., 10 figs.

  8. Advanced concepts for electromagnetic launcher power supplies incorporating magnetic flux compression

    SciTech Connect

    Driga, M.D. . Dept. of Electrical and Computer Engineering); Fair, H.D. )

    1991-01-01

    Electromagnetic coil launchers offer the potential for extremely high efficiency, flexible, noncontracting, hypervelocity electromagnetic accelerators. Unfortunately, their implementation and development has been severely limited by the lack of compact power supplies capable of providing the required high energy and high powers. Integrating novel magnetic flux compression features into multistage rotating machines provides the flexible means for generating tailored, high-energy, high-power electromagnetic pulses required to efficiently drive these promising coil launchers. This paper presents advanced concepts of high energy power supplies for coil launchers. These concepts are designed to produce high inductive compression ratios and large current and magnetic field multiplication ratios in the range of megamperes of current and gigawatts of active power. As a consequence of the flexibility of multiwinding rotating generators, such designs provide an extensive range of output pulse shaping in single or multiple pulses, enabling optimum operation of the coil launcher.

  9. WARP-10: A numerical simulation model for the cylindrical reconnection launcher

    SciTech Connect

    Widner, M.M.

    1989-01-01

    A fully self-consistent computer simulation code called WARP-10, used for modelling the Reconnection Launcher, is described. WARP-10 has been compared with various experiments with good agreement for performance and heating. Simulations predict that it is possible to obtain nearly uniform acceleration with high efficiency and low armature heating. There does not appear to be an armature heating limit to velocity provided the armature mass can be sufficiently large. Simulation results are presented which show it is possible to obtain conditions needed for Earth-to-Orbit (ETO) launch applications (4.15 km/s and a 950 kg launch mass). This 3100-stage launcher has an efficiency of 47.2% and a final ohmic energy/kinetic energy = .000146. The mode of launcher operation is similar to a traveling water induction launcher and is produced by properly times and tuned discrete stages. Further optimization and much high velocities appear possible. 15 refs., 6 figs.

  10. WARP-10; A numerical simulation model for the cylindrical reconnection launcher

    SciTech Connect

    Widner, M.M. )

    1991-01-01

    In this paper a fully self-consistent computer simulation code called WARP-10, used for modelling the Reconnection Launcher, is described. WARP-10 has been compared with various experiments with good agreement for performance and heating. Simulations predict that it is possible to obtain nearly uniform acceleration with high efficiency and low armature heating. There does not appear to be an armature heating limit to velocity provided the armature mass can be sufficiently large. Simulation results are presented which show it is possible to obtain conditions needed for Earth-to-Orbit (ETO) launch applications (4.15 km/s and a 850 kg launch mass). This 3100-stage launcher has an efficiency of 47.2% and a final ohmic energy/kinetic energy - .00146. The mode of launcher operation is similar to a traveling wave induction launcher and is produced by properly timed and tuned discrete stages. Further optimization and much higher velocities appear possible.

  11. Study of the modelling of an electromagnetic launcher of fire extinguishing loads

    NASA Astrophysics Data System (ADS)

    Frunzulica, Florin; Oncescu, Cosmin; Dumitrache, Alexandru; Vintea, Adela

    2016-06-01

    The problem of launchers used in civil applications is a topical issue. The role of a launcher is to launch objects with a certain speed towards certain goals like for example dangerous fire outbreaks (drilling areas, fires in buildings). This paper is aiming to present the theoretical aspects and results regarding the launching objects, in this case spheres that contains firefighting substance, during the launching stage, the ballistic stage and the impact stage with a solid surface.

  12. The PARA: A computer simulation code for plasma driven electromagnetic launchers

    NASA Astrophysics Data System (ADS)

    Thio, Y. C.

    1983-03-01

    A computer code for simulation of rail type accelerators utilizing a plasma armature was developed and is described in detail. Some time varying properties of the plasma are taken into account in this code thus allowing the development of a dynamical model of the behaviour of plasma in a rail type electromagnetic Launcher. The code is being successfully used to predict and analyze experiments on small calibre rail gun launchers.

  13. Preliminary analysis of space mission applications for electromagnetic launchers

    NASA Technical Reports Server (NTRS)

    Miller, L. A.; Rice, E. E.; Earhart, R. W.; Conlon, R. J.

    1984-01-01

    The technical and economic feasibility of using electromagnetically launched EML payloads propelled from the Earth's surface to LEO, GEO, lunar orbit, or to interplanetary space was assessed. Analyses of the designs of rail accelerators and coaxial magnetic accelerators show that each is capable of launching to space payloads of 800 KG or more. A hybrid launcher in which EML is used for the first 2 KM/sec followed by chemical rocket stages was also tested. A cost estimates study shows that one to two EML launches per day are needed to break even, compared to a four-stage rocket. Development models are discussed for: (1) Earth orbital missions; (2) lunar base supply mission; (3) solar system escape mission; (4) Earth escape missions; (5) suborbital missions; (6) electromagnetic boost missions; and (7) space-based missions. Safety factors, environmental impacts, and EML systems analysis are discussed. Alternate systems examined include electrothermal thrustors, an EML rocket gun; an EML theta gun, and Soviet electromagnetic accelerators.

  14. Visible light emission measurements from a dense electrothermal launcher plasma

    NASA Astrophysics Data System (ADS)

    Hankins, O. E.; Bourham, M. A.; Earnhart, J.; Gilligan, J. G.

    1993-01-01

    Measurements of the visible light emission from dense, weakly non-ideal plasmas have been performed on the experimental electrothermal launcher device 'SIRENS'. The plasma is created by the ablation or a Lexan insulator in the source, which then flows through a cylindrical barrel which serves as the material sample. Visible light emission spectra have been observed both in-bore and from the muzzle flash or the barrel, and from the flash or the source. Due to high plasma opacity (the plasma emits as a near blackbody) and absorption by the molecular components of the vapor shield, the hotter core or the arc has been difficult to observe. Recent measurements along the axis or the device indicate time-averaged plasma temperatures in the barrel or about 1 eV for lower energy shots, which agree with experimental measurements of the average heat flux and plasma conductivity along the barrel. Measurements or visible emission from the source indicate time averaged temperatures of 1 to 2 eV which agree with the theoretical estimates derived from ablated mass measurements and calculated estimates derived from plasma conductivity measurements.

  15. Studies to reduce material erosion in electrothermal launchers

    NASA Astrophysics Data System (ADS)

    Gilligan, J.; Bourham, M.; Hankins, O.; Auciello, O.; Tallavarjula, S.

    1991-01-01

    Plasma erosion processes on insulators and conductors, using the SIRENS electrothermal launcher, have verified the vapor shield concept. The energy transmission factor through the vapor shield was found to vary from 20 percent to 5 percent as the heat flux increases. Metals have strong axial erosion dependence, with an average erosion depth of 15-45 micron/kJ for aluminum and 5-10 micron/kJ for pure copper. Insulators have uniform ablation along the axial direction, with an average ablation depth of 10-14 micron/kJ for Lexan. Aluminum has a higher erosion rate with an increase of energy input, while Lexan and pure copper have approximately equal erosion rates which are considerably less than that of aluminum. High-density graphite does not ablate at lower energies, and ablates only slightly at energies above 3 kJ (1-2 micron/kJ), while molded dense electrographite ablates at a higher rate (1-3 micron/kJ). Both types of graphite have considerably less ablation than other materials. Lexan and graphites showed greater evidence of the vapor shield effect than aluminum and copper, although there is tendency toward less erosion at higher values of heat fluxes. Multiple exposure of material surfaces demonstrated that insulators have better performance than metallic surfaces.

  16. A small scale lunar launcher for early lunar material utilization

    NASA Technical Reports Server (NTRS)

    Snow, W. R.; Kubby, J. A.; Dunbar, R. S.

    1981-01-01

    A system for the launching of lunar derived oxygen or raw materials into low lunar orbit or to L2 for transfer to low earth orbit is presented. The system described is a greatly simplified version of the conventional and sophisticated approach suggested by O'Neill using mass drivers with recirculating buckets. An electromagnetic accelerator is located on the lunar surface which launches 125 kg 'smart' containers of liquid oxygen or raw materials into a transfer orbit. Upon reaching apolune a kick motor is fired to circularize the orbit at 100 km altitude or L2. These containers are collected and their payloads transferred to a tanker OTV. The empty containers then have their kick motors refurbished and then are returned to the launcher site on the lunar surface for reuse. Initial launch capability is designed for about 500T of liquid oxygen delivered to low earth orbit per year with upgrading to higher levels, delivery of lunar soil for shielding, or raw materials for processing given the demand.

  17. Developing a Launch Package for the PEGASUS Launcher

    NASA Astrophysics Data System (ADS)

    Hundertmark, S.; Vincent, G.; Simicic, D.

    2017-07-01

    Railguns are capable to far exceed the muzzle energies of current naval deck guns. Therefore one of the most promising scenario for the future application of railguns in naval warfare is the long range artillery. Hypervelocity projectiles being propelled to velocities above 2 km/s reach targets at distances of 200 km or more. At the French-German Research Institute the PEGASUS launcher is used for investigations with respect to this scenario. The 6 m long barrel has a square caliber of 40 mm. The power supply unit is able to deliver 10 MJ to the gun. Within this investigation, a complete launch package is being developed and experiments are performed that aim at showing that this package can be accelerated to velocities ranging from 2000 m/s to 2500 m/s. A launch package consists out of an armature, a sabot and the projectile. The armature ensures the electrical contact during launch and pushes the sabot with its payload through the barrel. The sabot guides and protects the payload during the acceleration. At the same time the accelerating forces generated at the armature needs to be transferred to the projectile. After the launch package has left the barrel, the sabot should open and release its payload, the projectile into free-flight. Here the current status of the launch package development and results from experiments with the PEGASUS railgun are presented.

  18. A small scale lunar launcher for early lunar material utilization

    NASA Technical Reports Server (NTRS)

    Snow, W. R.; Kubby, J. A.; Dunbar, R. S.

    1981-01-01

    A system for the launching of lunar derived oxygen or raw materials into low lunar orbit or to L2 for transfer to low earth orbit is presented. The system described is a greatly simplified version of the conventional and sophisticated approach suggested by O'Neill using mass drivers with recirculating buckets. An electromagnetic accelerator is located on the lunar surface which launches 125 kg 'smart' containers of liquid oxygen or raw materials into a transfer orbit. Upon reaching apolune a kick motor is fired to circularize the orbit at 100 km altitude or L2. These containers are collected and their payloads transferred to a tanker OTV. The empty containers then have their kick motors refurbished and then are returned to the launcher site on the lunar surface for reuse. Initial launch capability is designed for about 500T of liquid oxygen delivered to low earth orbit per year with upgrading to higher levels, delivery of lunar soil for shielding, or raw materials for processing given the demand.

  19. Development of an accelerating-piston implosion-driven launcher

    NASA Astrophysics Data System (ADS)

    Huneault, Justin; Loiseau, Jason; Higgins, Andrew

    2013-06-01

    The ability to soft-launch projectiles at velocities exceeding 10 km/s is of interest to several scientific fields, including orbital debris impact testing and equation of state research. Current soft-launch technologies have reached a performance plateau below this operating range. The energy and power density of high explosives provides a possible avenue to reach this velocity if used to dynamically compress a light driver gas to significantly higher pressures and temperatures compared to light-gas guns. In the implosion-driven launcher (IDL), linear implosion of a pressurized tube drives a strong shock into the gas ahead of the tube pinch, thereby forming an increasingly long column of compressed gas which can be used to propel a projectile. The McGill IDL has demonstrated the ability to launch a 0.1-g projectile to 9.1 km/s. This study focuses on the implementation of a novel launch cycle wherein the explosively driven pinch is accelerated down the length of the tube in order to maintain a relatively constant projectile base pressure early in the launch cycle. The experimental development of an accelerating driver which utilizes an explosive lens to phase the detonation wave is presented. The design and experimental performance of an accelerating-piston IDL is also discussed.

  20. Development of an accelerating piston implosion-driven launcher

    NASA Astrophysics Data System (ADS)

    Huneault, J.; Loiseau, J.; Higgins, A. J.

    2014-05-01

    The ability to soft-launch projectiles to velocities exceeding 10 km/s is of interest for a number of scientific fields, including orbital debris impact testing and equation of state research. Current soft-launch technologies have reached a performance plateau below this operating range. In the implosion-driven launcher (ILD) concept, explosives are used to dynamically compress a light driver gas to significantly higher pressures and temperatures than the propellant of conventional light-gas guns. The propellant of the IDL is compressed through the linear implosion of a pressurized tube. The imploding tube behaves like a piston which travels into the light gas at the explosive detonation velocity, thus forming an increasingly long column of shock-compressed gas which can be used to propel a projectile. The McGill designed IDL has demonstrated the ability to launch a 0.1-g projectile to 9.1 km/s. This work will focus on the implementation of a novel launch cycle in which the explosively driven piston is accelerated in order to gradually increase driver gas compression, thus maintaining a relatively constant projectile driving pressure. The theoretical potential of the concept as well as the experimental development of an accelerating piston driver will be examined.

  1. Rockot - a new cost effective launcher for small satellites

    NASA Astrophysics Data System (ADS)

    Mosenkis, Regina

    1996-01-01

    Daimler-Benz Aerospace of Germany and the Russian Khrunichev State Research and Production Space Center have formed a jointly owned EUROCKOT Launch Services GmbH to offer worldwide cost effective launch services for the ROCKOT launch vehicle. ROCKOT, produced by Khrunichev, builder of the famous PROTON launcher, aims at the market of small and medium size satellites ranging from 300 to 1800 kg to be launched into low earth or sunsynchronous orbits. These comprize scientific, earth observation and polar meteorological satellites as well as the new generation of small communication satellites in low earth orbits, known as the ``Constellations''. ROCKOT is a three stage liquid propellant launch vehicle, composed of a former Russian SS 19 strategic missile, which has been withdrawn from military use, and a highly sophisticated, flight-proven upper stage named Breeze, which is particularly suited for a variety of civic and commercial space applications. Usable payload envelope has a length of 4.75 meters and a maximum diameter of 2.26 meters for accomodating the payload within the payload fairing. ROCKOT can also accomodate multiple payloads which can be deployed into the same or different orbits. So far ROCKOT has been successfully launched three times from Baikonur. The commercial launch services on ROCKOT from the Plesetsk launch site, Russia, will begin in 1997 and will be available worldwide at a highly competitive price.

  2. High velocity electromagnetic particle launcher for aerosol production studies

    SciTech Connect

    Benson, D.A.; Rader, D.J.

    1986-05-01

    This report describes the development of a new device for study of metal combustion, breakup and production of aerosols in a high velocity environment. Metal wires are heated and electromagnetically launched with this device to produce molten metal droplets moving at velocities ranging up to about Mach 1. Such tests are presently intended to simulate the behavior of metal streamers ejected from a high-explosive detonation. A numerical model of the launcher performance in terms of sample properties, sample geometry and pulser electrical parameters is presented which can be used as a tool for design of specific test conditions. Results from several tests showing the range of sample velocities accessible with this device are described and compared with the model. Photographic measurements showing the behavior of tungsten and zirconium metal droplets are presented. Estimates of the Weber breakup and drag on the droplets, as well as calculations of the droplet trajectories, are described. Such studies may ultimately be useful in assessing environmental hazards in the handling and storage of devices containing metallic plutonium.

  3. 10. DRIVE TRUCK ASSEMBLY OF MOBILE SERVICE STRUCTURE IN POSITION ...

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

    10. DRIVE TRUCK ASSEMBLY OF MOBILE SERVICE STRUCTURE IN POSITION NEXT TO LAUNCHER BUILDING SHOWING CHASES, DUCTS, PIPES AND CONDUITS; VIEW TO NORTHWEST. - Cape Canaveral Air Station, Launch Complex 17, Facility 28501, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

  4. Ariane 5 launcher - coherency and integrity of prelaunch and in-flight electrical system operations by using a huge launcher functional data base

    NASA Astrophysics Data System (ADS)

    Auvray, G.

    The ARIANE 5 launcher is the new generation of the European ARIANE launcher family. It allows for a major improvement of the payload capacity and a better reliability. The ARIANE 5 avionics is fully redundant and uses new concepts for the redundancy design and the on-board software development. Linked with these concepts, a new approach has been developed related to stages and launch vehicle ground control and ground and in-flight launcher operations. Stages testing performed in EUROPE and GUIANA, and launch vehicle verification use similar hardware and software tools: the ARIANE 5 command and control bench (CCB). Both round and on-board software architectures allow one to perfectly isolate application software parts from launcher electrical system descriptions. This approach is mainly supported by the ARIANE 5 operational data base (BDO). After a short description of ARIANE 5 avionics and ground testing systems organization, this paper shows the data base structure, presents the different software tools which allow data base utilization to ground and on-board software's benefit, and demonstrates how this structure guarantees ground checking and in-flight operations.

  5. Zero Boil Off Cryogen Storage for Future Launchers

    NASA Technical Reports Server (NTRS)

    Valentian, D.; Plachta, D.; Kittel, P.; Hastings, L. J.; Salerno, Louis J.; Arnold, James O. (Technical Monitor)

    2001-01-01

    Zero boil off (ZBO) cryogen storage using both cryocoolers and passive insulation technologies will enable long-term exploration missions by allowing designers to optimize tankage without the need for excess cryogen storage to account for boil off. Studies of ZBO (zero boil off) have been on-going in the USA for several years. More recently, a review of the needs of advanced space propulsion took place in Europe. This showed the interest of the European community in cryogenic propulsion for planetary missions as well as the use of liquid hydrogen for large power electric propulsion (manned Mars missions). Although natural boiling could be acceptable for single leg missions, passive insulation techniques yield roughly a I% per month cryogen loss and this would not be cost effective for robotic planetary missions involving storage times greater than one year. To make economic sense, long-term exploration missions require lower tank capacity and longer storage times. Recent advances in cryocooler technology, resulting in vast improvements in both cooler efficiency and reliability, make ZBO is a clear choice for planetary exploration missions. Other, more near term applications of ZBO include boil-off reduction or elimination applied to first and upper stages of future earth-to-orbit (ETO) launchers. This would extend launch windows and reduce infrastructure costs. Successors to vehicles like Ariane 5 could greatly benefit by implementing ZBO. Zero Boil Off will only be successful in ETO launcher applications if it makes economic sense to implement. The energy cost is only a fraction of the total cost of buying liquid cryogen, the rest being transportation and other overhead. Because of this, higher boiling point cryogens will benefit more from on-board liquefaction, thus reducing the infrastructure costs. Since hydrogen requires a liquefier with at least a 17% efficiency just to break even from a cost standpoint, one approach for implementing ZBO in upper stages would

  6. A design study for the ECH launcher for ITER

    SciTech Connect

    Prater, R.; Grunloh, H.J.; Moeller, C.P.; Doane, J.L.; Olstad, R.A.; Makowski, M.A.; Harvey, R.W.

    1997-04-01

    The Design Description Document for ITER calls for 50 MW of electron cyclotron power at a frequency of 170 GHz, upgradeable to 100 MW. This power is intended to heat the plasma from Ohmic temperatures to ignition, in concert with power from some combination of neutral injection and/or ICRF heating. The second major application of ECH power is current drive. In the advanced steady-state scenarios, the total current is 12 to 16 MA, of which 75% is driven by bootstrap effects. The current drive requirement is 2 to 3 MA at a relative minor radius of 0.7, plus a small current near the center of the discharge. ECH power is also used for plasma initiation and startup, using a separate ECH system of two fixed frequencies between 90 to 140 GHz and total power to 6 MW. Suppression or control of MHD instabilities like neoclassical tearing modes, sawteeth, ELMs, and locked modes are also important objectives for the ECH systems. However, the launching and power characteristics of the ECH for these applications is highly specialized. The ability to modulate at high frequency (at least several tens of kHz), the ability to redirect the beams with precision at relatively high speed, and the requirement that the stabilization be carried out at the same time as the bulk heating and current drive imply that separate and specialized ECH systems are needed for the stabilization activities. For example, for stabilization of neoclassical tearing modes current must be driven inside the islands near the q = 2 surface. If this is done near the outboard mid plane, a system with optimized frequency might be much more effective than what could be done with the main 170 GHz system. This paper does not treat the launchers for the stabilization systems.

  7. Investigation of electromagnetic launcher behavior for impact fusion. Annual report, May 1, 1984-April 30, 1985

    SciTech Connect

    Thio, Y.C.

    1985-05-01

    The second year of a 4-year program to develop an ultra-high velocity electromagnetic launcher has been completed, with significant progress made in the key technical areas. This lays firmly the cornerstone for major progress in Year 3 of the program. The launcher instrumentation and diagnostics system was developed. More than 20 launcher experiments were conducted using the SUVAC-I augmented launcher system. We tested our novel plasma generation technique using a lithium seeded propellant with encouraging success. We accelerated a 1.4 g projectile to 5.3 km/s in 1.6 m in the series. Unaugmented barrels for SUVAC-II were fabricated. The barrels were tested and commissioned with a total of 8 firings in single-stage configurations. The tests verified the basic soundness of the barrel mechanical and electrical design. Velocity up to 4.4 km/s was achieved with a 1.1 g projectile. Concurrently, we completed the fabrication, assembly and installation of SUVAC-II power supply (1 MJ) and its expanded control system. Experimentation with the multi-stage SUVAC-II launcher is expected to take place in the early part of Year 3. In the meantime, fabrication of the SUVAC-III power supply (an additional 0.4 MJ) has also been initiated.

  8. Production of large-area surface-wave plasmas with an internally mounted planar cylindrical launcher

    NASA Astrophysics Data System (ADS)

    Nagatsu, M.; Naito, K.; Ogino, A.; Nanko, S.

    2006-02-01

    We studied the characteristics of two different types of planar cylindrical microwave launchers installed inside the vacuum chamber for the production of a large-area processing plasma. The microwave launcher consisted of a coaxial waveguide and a cylindrical planar cavity, inside which a large-area thin quartz plate was inserted. We tested two configurations of microwave launchers; one was a closed cylindrical cavity structure and the other was a leaky open cavity structure. With a 1.5 kW microwave source, we demonstrated the production of large-area, surface-wave plasma (SWP) using Ar gas. Using the microwave launcher with a leaky open cavity structure, a spatial uniformity of SWP within ±3.5% over 160 mm in radius was achieved at a pressure of 20 ~ 30 Pa. Numerical analyses using the electromagnetic wave simulator, MAFIA, were also carried out to study the electric field distribution radiated from the microwave launcher and to explain the experimental results.

  9. From Satellite To Launcher, Highlights On Powder/Wire ALM At Astrium Space Transportation

    NASA Astrophysics Data System (ADS)

    Bourenaud, Florent; Desagulier, Christian

    2012-07-01

    ALM (Additive Layer Manufacturing) or Direct Manufacturing has been one of EADS’ (and more recently Astrium ST’s) major interests for almost a decade. It consists in manufacturing a part by adding (metallic) material layer by layer instead of machining the desired shape from a blank. It therefore has many advantages directly suitable for the spatial business, ranging from satellite to launcher structures. The present paper describes the range of available additive processes suitable for our present or future metallic launcher structures. The operational domain is described, in close correlation with the specific spatial constraints. A first successful in-flight application has been recently demonstrated by Astrium ST, which clearly opens a wide range of opportunities for next generation launchers and satellite structures. This paper gives an overview of the (technically and economically) eligible spatial structures that represent strong ALM business cases, as well as the on-going R&T and development trends at Astrium ST

  10. International Space Station-Based Electromagnetic Launcher for Space Science Payloads

    NASA Technical Reports Server (NTRS)

    Jones, Ross M.

    2013-01-01

    A method was developed of lowering the cost of planetary exploration missions by using an electromagnetic propulsion/launcher, rather than a chemical-fueled rocket for propulsion. An electromagnetic launcher (EML) based at the International Space Station (ISS) would be used to launch small science payloads to the Moon and near Earth asteroids (NEAs) for the science and exploration missions. An ISS-based electromagnetic launcher could also inject science payloads into orbits around the Earth and perhaps to Mars. The EML would replace rocket technology for certain missions. The EML is a high-energy system that uses electricity rather than propellant to accelerate payloads to high velocities. The most common type of EML is the rail gun. Other types are possible, e.g., a coil gun, also known as a Gauss gun or mass driver. The EML could also "drop" science payloads into the Earth's upper

  11. A 150mm launcher facility for shockwave compression experiments: A critical review and conceptual design study

    NASA Astrophysics Data System (ADS)

    Swift, H. F.

    1981-01-01

    Lawrence Livermore Laboratory is considering construction of a large planar shockware facility using a 150 mm launcher. The facility will be used to study explosive initiation which places serious constraints upon facility design. It is recommended that the projectile be guided to the target along expendable plastic rails that will not produce shrapnel when shattered and allow the system to operate effectively under mild evacuation. The launcher employs an 18 m long launch tube with both solid propellant and cold-gas chambers to launch packages weighing up to 9 kg to velocities between 0.2 and 2 km/s. Unique hardware designs are suggested for coupling launch tube segments and connecting chambers. The launch tube is supported on a base via bearinged carts that allow 3 m of axial motion for maintenance/ assembly. Chambers are supported on carts that roll on floor-mounted rails during launchers assembly/disassembly and operation.

  12. Apparatus for and method of operating a cylindrical pulsed induction mass launcher

    DOEpatents

    Cowan, Jr., Maynard; Duggin, Billy W.; Widner, Melvin M.

    1992-01-01

    An electromagnetic cylindrical projectile mass launcher and a method of operation is provided which includes a cylindrical projectile having a conducting armature, a cylindrical barrel in which the armature is received, a plurality of electromagnetic drive coil stages, a plurality of pulse energy sources, and a pulsed power arrangement for generating magnetic pulses forming a pulsed magnetic wave along the length of the launcher barrel. The pulsed magnetic wave provides a propelling force on the projectile along the drive coil. The pulsed magnetic wave of the drive coil stages is advanced along the armature faster than the projectile to thereby generate an induced current wave in the armature. The pulsed generation of the magnetic wave minimizes electromagnetic heating of the projectile and provides for smooth acceleration of the projectile through the barrel of the launcher.

  13. Apparatus for and method of operating a cylindrical pulsed induction mass launcher

    DOEpatents

    Cowan, M. Jr.; Duggin, B.W.; Widner, M.M.

    1992-06-30

    An electromagnetic cylindrical projectile mass launcher and a method of operation is provided which includes a cylindrical projectile having a conducting armature, a cylindrical barrel in which the armature is received, a plurality of electromagnetic drive coil stages, a plurality of pulse energy sources, and a pulsed power arrangement for generating magnetic pulses forming a pulsed magnetic wave along the length of the launcher barrel. The pulsed magnetic wave provides a propelling force on the projectile along the drive coil. The pulsed magnetic wave of the drive coil stages is advanced along the armature faster than the projectile to thereby generate an induced current wave in the armature. The pulsed generation of the magnetic wave minimizes electromagnetic heating of the projectile and provides for smooth acceleration of the projectile through the barrel of the launcher. 2 figs.

  14. Integrated plasmonic semi-circular launcher for dielectric-loaded surface plasmon-polariton waveguide.

    PubMed

    Li, Xiaowei; Huang, Lingling; Tan, Qiaofeng; Bai, Benfeng; Jin, Guofan

    2011-03-28

    A semi-circular plasmonic launcher integrated with dielectric-loaded surface plasmon-polaritons waveguide (DLSPPW) is proposed and analyzed theoretically, which can focus and efficiently couple the excited surface plasmon polaritons (SPPs) into the DLSPPW via the highly matched spatial field distribution with the waveguide mode in the focal plane. By tuning the incident angle or polarization of the illuminating beam, it is shown that the launcher may be conveniently used as a switch or a multiplexer that have potential applications in plasmonic circuitry. Furthermore, from an applicational point of view, it is analyzed how the coupling performance of the launcher can be further improved by employing multiple semi-circular slits.

  15. Results from Sandia National Laboratories/Lockheed Martin Electromagnetic Missile Launcher (EMML).

    SciTech Connect

    Lockner, Thomas Ramsbeck; Skurdal, Ben; Gaigler, Randy; Basak, L; Root, G; Aubuchon, Matthew S.; Turman, Bobby N.; Floyd, Mendel D.

    2005-05-01

    Sandia national laboratories (SNL) and lockheed martin MS2 are designing an electromagnetic missile launcher (EMML) for naval applications. The EMML uses an induction coilgun topology with the requirement of launching a 3600 lb. missile up to a velocity of 40 m/s. To demonstrate the feasibility of the electromagnetic propulsion design, a demonstrator launcher was built that consists of approximately 10% of the propulsion coils needed for a tactical design. The demonstrator verified the design by launching a 1430 lb weighted sled to a height of 24 ft in mid-December 2004 (Figure 1). This paper provides the general launcher design, specific pulsed power system component details, system operation, and demonstration results.

  16. LAUNCHER PERFORMANCE AND THERMAL CAPABILITY OF THE DIII-D ECH SYSTEM

    SciTech Connect

    KAJIWARA,K; LOHR,J; GORELOV,I.A; GREEN,M.T; PONCE,D; CALLIS,R.W; ELLIS,R.A

    2003-10-01

    OAK-B135 The temperatures of components of DIII-D ECH launchers were observed during 2003 tokamak operation. The injected power was typically 500-700 kW and the pulse length was typically 2s. Plasma shots were performed at intervals of about 17 min from 9 a.m. to 5 p.m. The temperatures of a movable mirror, a fixed mirror and a launcher reached an equilibrium after about six hours of repetitive pulsing. The saturation temperature depends to some extent on the plasma stored energy. However, even in high {beta} plasma, the temperatures plateaued at acceptable values.

  17. Test results for three prototype models of a linear induction launcher

    SciTech Connect

    Zabar, Z.; Lu, X.N.; He, J.L.; Birenbaum, L.; Levi, E.; Kuznetsov, S.B.; Nahemow, M.D. )

    1991-01-01

    This paper reports on the work on the linear induction launcher (LIL) started with an analytical study tht was followed by computer simulations and then was tested by laboratory models. Two mathematical representations have been developed to describe the launcher. The first, based on the field approach with sinusoidal excitation, has been validated by static tests on a small scale prototype fed at constant current and variable frequency. The second, a transient representation using computer simulation allows consideration of energization by means of a capacitor bank and a power conditioner. Tests performed on three small-scale prototypes up to 100 m/s muzzle velocities show good agreement with predicted performance.

  18. The LHCD Launcher for Alcator C-Mod - Design, Construction, Calibration and Testing

    SciTech Connect

    J. Hosea; D. Beals; W. Beck; S. Bernabei; W. Burke; R. Childs; R. Ellis; E. Fredd; N. Greenough; M. Grimes; D. Gwinn; J. Irby; S. Jurczynski; P. Koert; C.C. Kung; G.D. Loesser; E. Marmar; R. Parker; J. Rushinski; G. Schilling; D. Terry; R. Vieira; J.R. Wilson; J. Zaks

    2005-06-27

    MIT and PPPL have joined together to fabricate a high-power lower hybrid current drive (LHCD) system for supporting steady-state AT regime research on Alcator C-Mod. The goal of the first step of this project is to provide 1.5 MW of 4.6 GHz rf [radio frequency] power to the plasma with a compact launcher which has excellent spectral selectivity and fits into a single C-Mod port. Some of the important design, construction, calibration and testing considerations for the launcher leading up to its installation on C-Mod are presented here.

  19. 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.

  20. Survivability of the Hardened Mobile Launcher When Attacked by a Hypothetical Rapidly Retargetable ICBM System.

    DTIC Science & Technology

    1986-03-01

    condition which exists when no strategic power believes it can significantly improve its situation by attacking first in a crisis or when it does not feel...98% chance of killing the HML (again, refer to Figure 20). ,: Mn- A. ,1~** :; ’,rter-lily P’iiurt- 0 i u"rjnlifive Lo -. iN,:,rrnal N:.rn. ,.e Furt,-t...Fiqurie 26 Variations in Speed for the 5 Warhead Case 7T% Lo pe Base Case 7 ~High ’Speed 0 5 10 15 02 Cycle Time (Minutes) Fiqure 27 ’Variation in Speed

  1. Mount mechanisms for the Saturn 5/Apollo mobile launcher at John F. Kennedy Space Center

    NASA Technical Reports Server (NTRS)

    Balke, H. A.

    1975-01-01

    A support system was designed to resist hurricane wind loads at the launch pad and to allow the supported structural frame to expand and contract freely under wide ranges of temperature. This system consists of six mount mechanisms devised to meet the previously stated requirements plus a load-carrying capacity for each of 3.2-million kilograms (7-million pounds) downward and 1.6-million kilograms (3.5-million pounds) upward. A similar but lighter system of six mount mechanisms was designed for use in the sheltered environment of the vehicle assembly building. Each requirement and design result is discussed, and each mount mechanism is defined by location and type with references to visual presentations.

  2. Design and Characterization of Thin Stainless Steel Burst Disks for Increasing Two-Stage Light Gas Launcher Efficiency

    NASA Technical Reports Server (NTRS)

    Tylka, Jonathan M.; Johnson, Kenneth L.; Henderson, Donald; Rodriguez, Karen

    2012-01-01

    Laser etched 300 series Stainless Steel Burst Disks (SSBD) ranging between 0.178 mm (0.007-in.) and 0.508mm (0.020-in.) thick were designed for use in a 17-caliber two-stage light gas launcher. First, a disk manufacturing method was selected using a combination of wire electrical discharge machining (EDM) to form the blank disks and laser etching to define the pedaling fracture pattern. Second, a replaceable insert was designed to go between the SSDB and the barrel. This insert reduced the stress concentration between the SSBD and the barrel, providing a place for the petals of the SSDB to open, and protecting the rifling on the inside of the barrel. Thereafter, a design of experiments was implemented to test and characterize the burst characteristics of SSBDs. Extensive hydrostatic burst testing of the SSBDs was performed to complete the design of experiments study with one-hundred and seven burst tests. The experiment simultaneously tested the effects of the following: two SSBD material states (full hard, annealed); five SSBD thicknesses 0.178, 0.254, 0.305, 0.381 mm (0.007, 0.010, 0.012, 0.015, 0.020-in.); two grain directions relative); number of times the laser etch pattern was repeated (varies between 5-200 times); two heat sink configurations (with and without heat sink); and, two barrel configurations (with and without insert). These tests resulted in the quantification of the relationship between SSBD thickness, laser etch parameters, and desired burst pressure. Of the factors investigated only thickness and number of laser etches were needed to develop a mathematical relationship predicting hydrostatic burst pressure of disks using the same barrel configuration. The fracture surfaces of two representative SSBD bursts were then investigated with a scanning electron microscope, one burst hydrostatically in a fixture and another dynamically in the launcher. The fracture analysis verified that both burst conditions resulted in a ductile overload failure

  3. Preliminary feasibility assessment for Earth-to-space electromagnetic (Railgun) launchers

    NASA Technical Reports Server (NTRS)

    Rice, E. E.; Miller, L. A.; Earhart, R. W.

    1982-01-01

    An Earth to space electromagnetic (railgun) launcher (ESRL) for launching material into space was studied. Potential ESRL applications were identified and initially assessed to formulate preliminary system requirements. The potential applications included nuclear waste disposal in space, Earth orbital applications, deep space probe launchers, atmospheric research, and boost of chemical rockets. The ESRL system concept consisted of two separate railgun launcher tubes (one at 20 deg from the horizontal for Earth orbital missions, the other vertical for solar system escape disposal missions) powered by a common power plant. Each 2040 m launcher tube is surrounded by 10,200 homopolar generator/inductor units to transmit the power to the walls. Projectile masses are 6500 kg for Earth orbital missions and 2055 kg for nuclear waste disposal missions. For the Earth orbital missions, the projectile requires a propulsion system, leaving an estimated payload mass of 650 kg. For the nuclear waste disposal in space mission, the high level waste mass was estimated at 250 kg. This preliminary assessment included technical, environmental, and economic analyses.

  4. Rocket launcher: A novel reduction technique for posterior hip dislocations and review of current literature.

    PubMed

    Dan, Michael; Phillips, Alfred; Simonian, Marcus; Flannagan, Scott

    2015-06-01

    We provide a review of literature on reduction techniques for posterior hip dislocations and present our experience with a novel technique for the reduction of acute posterior hip dislocations in the ED, 'the rocket launcher' technique. We present our results with six patients with prosthetic posterior hip dislocation treated in our rural ED. We recorded patient demographics. The technique involves placing the patient's knee over the shoulder, and holding the lower leg like a 'Rocket Launcher' allow the physician's shoulder to work as a fulcrum, in an ergonomically friendly manner for the reducer. We used Fisher's t-test for cohort analysis between reduction techniques. Of our patients, the mean age was 74 years (range 66 to 85 years). We had a 83% success rate. The one patient who the 'rocket launcher' failed in, was a hemi-arthroplasty patient who also failed all other closed techniques and needed open reduction. When compared with Allis (62% success rate), Whistler (60% success rate) and Captain Morgan (92% success rate) techniques, there was no statistically significant difference in the successfulness of the reduction techniques. There were no neurovascular or periprosthetic complications. We have described a reduction technique for posterior hip dislocations. Placing the patient's knee over the shoulder, and holding the lower leg like a 'Rocket Launcher' allow the physician's shoulder to work as a fulcrum, thus mechanically and ergonomically superior to standard techniques. © 2015 Australasian College for Emergency Medicine and Australasian Society for Emergency Medicine.

  5. High-Efficiency Helical Coil Electromagnetic Launcher and High Power Hall-Effect Switch

    DTIC Science & Technology

    2008-02-29

    as heat or acoustically as in arc blast when the projectile exits the launcher). If the EML is operated in ZC mode, then the stored energy can be used...mass ratio and provides magnetic levitation to the projectile. The mechanical aspects of the HCEL design should be investigated in the future. The hall

  6. Advanced concepts. [specific impulse, mass drivers, electromagnetic launchers, and the rail gun

    NASA Technical Reports Server (NTRS)

    Banks, B. A.

    1980-01-01

    The relative strengths of those interactions which enable propulsive forces are listed as well as the specific impulse of various propellants. Graphics show the linear synchronous motor of the mass driver, the principle of the direct current electromagnetic launcher, and the characteristics of the rail gun.

  7. Optimization of the ITER electron cyclotron equatorial launcher for improved heating and current drive functional capabilities

    SciTech Connect

    Farina, D.; Figini, L.; Henderson, M.; Saibene, G.

    2014-06-15

    The design of the ITER Electron Cyclotron Heating and Current Drive (EC H and CD) system has evolved in the last years both in goals and functionalities by considering an expanded range of applications. A large effort has been devoted to a better integration of the equatorial and the upper launchers, both from the point of view of the performance and of the design impact on the engineering constraints. However, from the analysis of the ECCD performance in two references H-mode scenarios at burn (the inductive H-mode and the advanced non-inductive scenario), it was clear that the EC power deposition was not optimal for steady-state applications in the plasma region around mid radius. An optimization study of the equatorial launcher is presented here aiming at removing this limitation of the EC system capabilities. Changing the steering of the equatorial launcher from toroidal to poloidal ensures EC power deposition out to the normalized toroidal radius ρ ≈ 0.6, and nearly doubles the EC driven current around mid radius, without significant performance degradation in the core plasma region. In addition to the improved performance, the proposed design change is able to relax some engineering design constraints on both launchers.

  8. Wave launcher heating studies in the ion cyclotron frequency range. Progress report

    SciTech Connect

    Scharer, J.E.

    1986-08-01

    This progress report discusses our work on the analysis, design, fabrication and laboratory measurements on ion cyclotron frequency range (ICRF) waveguide launchers. We have developed a computer code to solve for the surface impedance for a fast ICRF wave emanating from a dielectric filled guide in the presence of a divertor H-mode or L-mode plasma edge density profile. The H-mode with a density pedestal causes an increased, although tolerable wave reflection from the plasma. We have also formulated a computer code to analyze both vacuum ridged and folded-guide launchers. We have published work on scattering matrix formalism and developed a computer code to determine the coax probe size and distance to a sliding short to match the incident coax wave to the outgoing plasma ICRF wave emanating from the guide for general plasma impedances. We have made detailed measurements on a fabricated waveguide launcher for the cases of both air and de-ionized, distilled water-filled guides. The coax to waveguide transition for the matched water-filled dielectric guide case has a minimum power reflection coefficient of 6.3% at 90.8 MHz. We have also begun to consider coupling from ion Bernstein wave, folded and ridged vacuum-filled waveguide launchers.

  9. Environmental Assessment for the Space Complex-5 SCOUT Launcher Relocation, Vandenberg Air Force Base, California

    DTIC Science & Technology

    2009-01-01

    itself an endangered species, the buckwheat is. however. the host plant for an ESA-listed buttertly, the EI Segundo Blue Butterfly. Because this...endangered butterf!) relies on this host plant for part of its life cycle, this buckwheat is generally treated as a protected species. The SCOUT Launcher and

  10. Further investigations of plasma armature performance in the Culham Laboratory HTF rail launcher

    NASA Astrophysics Data System (ADS)

    Herring, N.; Spikings, C. R.; Oxley, C. M.; Beacham, J. R.; Putley, D.

    1993-01-01

    This paper presents the results from an experimental investigation of plasma armature behavior in the Culham Laboratory HTF rail launcher. The object of this work was to gain further insight into the conditions which lead to the formation of secondary plasma arcs in the rail launcher. The railgun was operated with a 1 cm square bore formed from glass reinforced epoxy insulators and either stainless steel or copper rails. A 1 MJ, 8 kV capacitor bank was used as the power supply; this was arranged in five 200 kJ modules. The modules were sequentially fired, to produce a current waveform approximating to a linear ramp in the railgun. B-dot probes were used to measure the behavior of the plasma armatures in the launcher. A number of calibration checks were performed to assess the quality of the B-dot probe measurements, with regard to both spatial resolution and rail current measurement. Experimental results were obtained with projectile muzzle velocities ranging from 1.5 km/s to 3.0 km/s, two free arc shots also occurred during the test series. The results show that the launcher performed much better with copper rails than with stainless steel rails. The results also show that the glass epoxy insulators performed much better than the acetyl copolymer material previously used in HTF.

  11. Flow structure and unsteadiness in the supersonic wake of a generic space launcher

    NASA Astrophysics Data System (ADS)

    Schreyer, Anne-Marie; Stephan, Sören; Radespiel, Rolf

    2015-11-01

    At the junction between the rocket engine and the main body of a classical space launcher, a separation-dominated and highly unstable flow field develops and induces strong wall-pressure oscillations. These can excite structural vibrations detrimental to the launcher. It is desirable to minimize these effects, for which a better understanding of the flow field is required. We study the wake flow of a generic axisymmetric space-launcher model with and without propulsive jet (cold air). Experimental investigations are performed at Mach 2.9 and a Reynolds number ReD = 1 . 3 .106 based on model diameter D. The jet exits the nozzle at Mach 2.5. Velocity measurements by means of Particle Image Velocimetry and mean and unsteady wall-pressure measurements on the main-body base are performed simultaneously. Additionally, we performed hot-wire measurements at selected points in the wake. We can thus observe the evolution of the wake flow along with its spectral content. We describe the mean and turbulent flow topology and evolution of the structures in the wake flow and discuss the origin of characteristic frequencies observed in the pressure signal at the launcher base. The influence of a propulsive jet on the evolution and topology of the wake flow is discussed in detail. The German Research Foundation DFG is gratefully acknowledged for funding this research within the SFB-TR40 ``Technological foundations for the design of thermally and mechanically highly loaded components of future space transportation systems.''

  12. Performance of the ECH Transmission Lines and Launchers in DIII-D

    SciTech Connect

    Kajiwara, K.; Mui, A.; Baxi, C.B.; Lohr, J.; Gorelov, I.A.; Green, M.T.; Ponce, D.; Callis, R.W.

    2005-09-26

    The efficiency of the transmission line for the 110 GHz ECH system was measured in DIII-D using a low power rf source. The measured efficiency was about 10% lower than expected from theoretical analysis of the components. The launcher temperature increase during rf pulses was measured and the peak mirror surface temperature was inferred from a simulation.

  13. Apparatus for and method of operating a cylindrical pulsed induction mass launcher

    SciTech Connect

    Cowan, M. Jr.; Duggin, B.W.; Widner, M.M.

    1990-12-06

    In accordance with the one aspect of the invention, an electromagnetic projectile launcher is provided which comprises: a conducting projectile, a barrel that receives the projectile, a plurality of electromagnetic drive coils, a plurality of pulsed energy sources, and pulse power means for generating a sequence of pulses forming a pulsed magnetic wave within the drive coil for propelling the projectile along the barrel, wherein the pulsed magnetic wave of the drive coil is advanced along the barrel faster than the projectile to thereby induce a current wave in the armature of the projectile and thereby minimize electromagnetic heating of the projectile and provide nearly constant acceleration of the projectile. In accordance with another aspect of the invention, a method is provided for propelling a projectile within a pulsed induction electromagnetic coil launcher, wherein the method comprises the steps of: generating a sequence of pulses forming a pulsed magnetic wave within the coil launcher, applying the pulsed magnetic wave initially at the aft end of the projectile to accelerate the projectile within the coil launcher, and advancing the position of the pulsed magnetic wave relative to the projectile to thereby generate an induced current wave in the armature, such that electromagnetic heating of the projectile is minimized and acceleration is nearly constant.

  14. Modeling electromagnetic rail launchers at speed using 3D finite elements

    SciTech Connect

    Rodger, D.; Leonard, P.J.; Eastham, J.F. )

    1991-01-01

    In this paper a new finite element technique for modelling 3D transient eddy currents in moving conductors is described. This has been implemented in the MEGA software package for 2 and 3D electromagnetic field analysis. The application of the technique to railgun launchers is illustrated.

  15. Free transverse vibration analysis of an underwater launcher based on fluid-structure interaction

    NASA Astrophysics Data System (ADS)

    Niu, Qingyong; Li, Tianyun; Zhu, Xiang; Wang, Lu

    2014-06-01

    A pneumatic launcher is theoretically investigated to study its natural transverse vibration in water. Considering the mass effect of the sealing cover, the launcher is simplified as a uniform cantilever beam with a top point mass. By introducing the boundary and continuity conditions into the motion equation, the natural frequency equation and the mode shape function are derived. An iterative calculation method for added mass is also presented using the velocity potential function to account for the mass effect of the fluid on the launcher. The first 2 order natural frequencies and mode shapes are discussed in external flow fields and both external and internal flow fields. The results show good agreement with both natural frequencies and mode shapes between the theoretical analysis and the FEM studies. Also, the added mass is found to decrease with the increase of the mode shape orders of the launcher. And because of the larger added mass in both the external and internal flow fields than that in only the external flow field, the corresponding natural frequencies of the former are relatively smaller.

  16. Advanced Optics for a Full Quasi-Optical Front Steering ECRH Upper Launcher for ITER

    SciTech Connect

    Moro, A.; Alessi, E.; Bruschi, A.; Platania, P.; Sozzi, C.; Chavan, R.; Collazos, A.; Goodman, T. P.; Udintsev, V. S.; Henderson, M. A.

    2009-11-26

    A full quasi-optical setup for the internal optics of the Front Steering Electron Cyclotron Resonance Heating (ECRH) Upper Launcher for ITER was designed, proving to be feasible and favorable in terms of additional flexibility and cost reduction with respect to the former design. This full quasi-optical solution foresees the replacement of the mitre-bends in the final section of the launcher with dedicated free-space mirrors to realize the last changes of directions in the launcher. A description of the launcher is given and its advantages presented. The parameters of the expected output beams as well as preliminary evaluations of truncation effects with the physical optics GRASP code are shown. Moreover, a study of mitre-bends replacement with single mirrors for multiple beams is described. In principle it could allow the beams to be larger at the mirror locations (with a further decrease of the peak power density due to partial overlapping) and has the additional advantage to get a larger opening with compressed beams to avoid conflicts with side-walls port. Constraints on the setup, arising both from the resulting beam characteristics in the space of free parameters and from mechanical requirements are taken into account in the analysis.

  17. Design, and initial experiment results of a novel LH launcher on Alcator C-Mod

    NASA Astrophysics Data System (ADS)

    Shiraiwa, S.; Meneghini, O.; Parker, R. R.; Wallace, G.; Wilson, J.; Faust, I.; Lau, C.; Mumgaard, R.; Scott, S.; Wukitch, S.; Beck, W.; Doody, J.; Irby, J.; MacGibbon, P.; Johnson, D.; Kanojia, A.; Koert, P.; Terry, D.; Vieira, R.; Alcator C-Mod Team

    2011-10-01

    The design, construction and initial results of a new lower hybrid current drive (LHCD) launcher on Alcator C-Mod (Hutchinson et al 1994 Phys. Plasmas 1 1511) are presented. The new LHCD launcher (LH2) is based on a novel splitter concept which evenly distributes the microwave power in four ways in the poloidal direction. This design allows for simplification of the feeding structure while keeping the flexibility to vary the peak launched toroidal index of refraction, Ntoroidal, from -3.8 to 3.8. An integrated model predicts good plasma coupling over a wide range of edge densities, while poloidal variations of the edge density are found to affect the evenness of power splitting in the poloidal direction. The measured transmission loss is about 30% lower than the previous launcher, and a clean Ntoroidal spectrum has been confirmed. Power handling capability exceeding an empirical weak conditioning limit and reliable operation up to 1.1 MW net LHCD power have been achieved. A survey of antenna-plasma coupling shows the existence of a millimetric vacuum gap in front of the launcher. Fully non-inductive, reversed shear plasma operation has been demonstrated and sustained for multiple current diffusion times. The current drive efficiency, ηLH ≡ neR0Ip/PLH, of these plasmas is (0.2-0.25) × 1020 m-2A W-1, which is in agreement with the expected efficiency on the International Thermonuclear Experimental Reactor (ITER).

  18. Status of next generation expendable launchers concepts within the FLPP program

    NASA Astrophysics Data System (ADS)

    Letourneur, Yann; Leleu, Frederic; Pinard, Didier; Krueger, Joerg; Balduccini, Mauro

    2010-05-01

    In the framework of the preparation of the next generation of launchers to be developed in Europe, the European Space Agency (ESA) has contracted NGL Prime and its industrial team to conduct a first slice of launch system and stage design activities and programmatic analyses for two types of launchers: A new expendable mid-term launch system relying on elements or "Building Blocks" from Ariane and Vega to be operational by 2015. A new long-term launch system called the Next Generation Launcher (NGL) to be operational by 2020-2025. The design reference missions include a 5 metric tons performance requirement into a Geostationary Transfer Orbit (GTO), to meet the European institutional need, with the increased capability to 8 metric tons into GTO by the addition of solid boosters, to meet the commercial market needs. In a first step, a series of trade-offs were conducted to select the concepts that best fit the requirements of the NGL and "Building Block" launcher options, in terms of propulsion (thrust level, engine characteristics), propellant choice (hydrogen, methane or solid propellants), launcher architecture (with or without strap-on boosters, bi or three stages architecture). In a second step, more detailed analyses were carried out in term of thermo-mechanical design, functional architecture, as well as in term of versatility capacity, i.e. the capability of the launcher to perform different missions than the reference ones. Consistently with this technical activity, a programmatic evaluation was consolidated by the industrial team. This paper details the outcomes of the activity carried out during this second step targeting at selecting one or two concepts. The paper will also give an overview and first results of the follow-on contract in which selected NGL concepts are being further investigated, in the prospect of creating a new European launcher family encompassing versions dedicated to the institutional needs and the commercial market (reference

  19. Development of Jettisonable Fluid Ground Connector for the ESA Next Generation Launcher Cryogenic Upper Stage

    NASA Astrophysics Data System (ADS)

    Eaton, Nick

    2014-06-01

    RUAG Space have successfully designed, developed and tested a new cryogenic connector sub-system for Hydrogen and Oxygen Filling and Venting of a potential launcher Upper Stage tank. The work was performed within the ESA Cryogenic Upper Stage Technologies, Future Launchers Preparatory Programme. The scope of the work was the development of this technology within Europe to a Technology Readiness Level of 5. Basic requirements were that the connector is jettisoned at lift-off, and that the filling of tanks located within the payload fairing volume is feasible. Beginning with concept studies, basic approaches were described and traded off, and more detailed designs and analyses performed for selected concepts. Experimental validation of the connector design was performed using extensive testing to simulate the fluid, mechanical, dynamic and thermal environments of the connector in pre-launch, lift-off and flight conditions.

  20. Design and evaluation of coils for a 50 mm diameter induction coilgun launcher

    SciTech Connect

    Kaye, R.J.; Shokair, I.R.; Wavrik, R.W.; Dempsey, J.F.; Honey, W.E.; Shimp, K.J.; Douglas, G.M.

    1993-12-31

    Coilguns have the ability to provide magnetic pressure to projectiles which results in near constant acceleration. However, to achieve this performance and control projectile hearing, significant constraints are placed on the design of the coils. We are developing coils to produce an effective projectile base pressure of 100 MPa (1kbar) as a step toward reaching base pressures of 200 MPa. The design uses a scalable technology applicable to the entire range of breech to muzzle coils of a multi-stage launcher. This paper presents the design of capacitor-driven coils for launching nominal 50 mm, 350 gram projectiles. Design criteria, constraints, mechanical stress analysis, launcher performance, and test results are discussed.

  1. Appraisal of UTIAS implosion-driven hypervelocity launchers and shock tubes.

    NASA Technical Reports Server (NTRS)

    Glass, I. I.

    1972-01-01

    A critical appraisal is made of the design, research, development, and operation of the novel UTIAS implosion-driven hypervelocity launchers and shock tubes. Explosively driven (PbN6-lead azide, PETN-pentaerythritetetranitrate) implosions in detonating stoichiometric hydrogen-oxygen mixtures have been successfully developed as drivers for hypervelocity launchers and shock tubes in a safe and reusable facility. Intense loadings at very high calculated pressures, densities, and temperatures, at the implosion center, cause severe problems with projectile integrity. Misalignment of the focal point can occur and add to the difficulty in using small caliber projectiles. In addition, the extreme driving conditions cause barrel expansion, erosion, and possible gas leakage from the base to the head of the projectile which cut the predicted muzzle velocities to half or a third of the lossless calculated values. However, in the case of a shock-tube operation these difficulties are minimized or eliminated and the possibilities of approaching Jovian reentry velocities are encouraging.

  2. A Monte Carlo Analysis for Collision Risk Assessment on Vega Launcher Payloads and LARES Satellite

    NASA Astrophysics Data System (ADS)

    Sindoni, G.; Ciufolini, I.; Battie, F.

    2016-03-01

    This work has been developed in the framework of the LARES mission of the Italian Space Agency (ASI). The LARES satellite has been built to test, with high accuracy, the frame-dragging effect predicted by the theory of General Relativity, specifically the Lense-Thirring drag of its node. LARES was the main payload in the qualification flight of the European Space Agency launcher VEGA. A concern arose about the possibility of an impact between the eight secondary payloads among themselves, with LARES and with the last stage of the launcher (AVUM). An impact would have caused failure on the payloads and the production of debris in violation of the space debris mitigation measures established internationally. As an additional contribution, this study allowed the effect of the payload release on the final manoeuvers of the AVUM to be understood.

  3. Angry Birds realized: water balloon launcher for teaching projectile motion with drag

    NASA Astrophysics Data System (ADS)

    Edwards, Boyd F.; Sam, David D.; Christiansen, Michael A.; Booth, William A.; Jessup, Leslie O.

    2014-05-01

    A simple, collapsible design for a large water balloon slingshot launcher features a fully adjustable initial velocity vector and a balanced launch platform. The design facilitates quantitative explorations of the dependence of the balloon range and time of flight on the initial speed, launch angle, and projectile mass, in an environment where quadratic air drag is important. Presented are theory and experiments that characterize this drag, and theory and experiments that characterize the nonlinear elastic energy and hysteresis of the latex tubing used in the slingshot. The experiments can be carried out with inexpensive and readily available tools and materials. The launcher provides an engaging way to teach projectile motion and elastic energy to students of a wide variety of ages.

  4. ITER ECH launcher options for start-up assist, bulk heating, and EC current drive experiments

    SciTech Connect

    Bigelow, T.S.

    1994-03-01

    Electron Cyclotron Heating (ECH) is proposed for providing plasma start-up, bulk heating, current drive, and other applications on the International Tokamak Experimental Reactor (ITER) project. The requirements for ECH power launching systems for ITER have been investigated, and several possible configurations that have been devised are described in this report. The proposed launcher designs use oversized circular corrugated waveguides that make small penetrations through the blanket modules and radiate into the plasma. The criteria used for the design calls for minimum blanket penetration area, maximum reliability, and optimum launched beam quality. The effects of the harsh plasma edge environment on the launcher are discussed. Power generation systems, windows, and other components of the ECH systems are also investigated. The designs presented are believed to be capable of operating reliably and are relatively easy to maintain remotely.

  5. Appraisal of UTIAS implosion-driven hypervelocity launchers and shock tubes.

    NASA Technical Reports Server (NTRS)

    Glass, I. I.

    1972-01-01

    A critical appraisal is made of the design, research, development, and operation of the novel UTIAS implosion-driven hypervelocity launchers and shock tubes. Explosively driven (PbN6-lead azide, PETN-pentaerythritetetranitrate) implosions in detonating stoichiometric hydrogen-oxygen mixtures have been successfully developed as drivers for hypervelocity launchers and shock tubes in a safe and reusable facility. Intense loadings at very high calculated pressures, densities, and temperatures, at the implosion center, cause severe problems with projectile integrity. Misalignment of the focal point can occur and add to the difficulty in using small caliber projectiles. In addition, the extreme driving conditions cause barrel expansion, erosion, and possible gas leakage from the base to the head of the projectile which cut the predicted muzzle velocities to half or a third of the lossless calculated values. However, in the case of a shock-tube operation these difficulties are minimized or eliminated and the possibilities of approaching Jovian reentry velocities are encouraging.

  6. Rf modeling and design of a folded waveguide launcher for the Alcator C-Mod tokamak

    SciTech Connect

    Bigelow, T.S.; Fogelman, C.F.; Baity, F.W.; Carter, M.D.; Hoffman, D.J.; Ryan, P.M.; Yugo, J.J.; Golovato, S.N.; Bonoli, P.

    1993-12-01

    The folded waveguide (FWG) launcher is being investigated as an improved antenna configuration for plasma heating in the ion cyclotron range of frequencies (ICRF). A development FWG launcher was successfully tested at Oak Ridge National Laboratory (ORNL) with a low-density plasma load and found to have significantly greater power density capability than current strap-type antennas operating in similar plasmas. To further test the concept on a high density tokamak plasma, a collaboration has been set up between ORNL and Massachusetts Institute of Technology (MIT) to develop and test an 80-MHz, 2-MW FWG on the Alcator C-Mod tokamak at MIT. The radio frequency (rf) electromagnetic modeling techniques and laboratory measurements used in the design of this antenna are described in this paper. A companion paper describes the mechanical design of the FWG.

  7. Projectile and rail launcher design analysis for electromagnetic propulsion to velocities exceeding 10 km/s

    SciTech Connect

    Buckingham, A.C.

    1981-02-24

    Hypersonic projectile launch was achieved using thrust exerted by an expanding electromagnetic field acting on the projectile base. Previous designs were confined to simple parallel-opposing flat rails. The rails carried the induction current used to launch rectangular projectiles. The projectiles weighed up to several grams and were launched at nearly 10 km/s. Here, a revised design for the launcher and projectiles using a more conventional cylindrical bore is described. Projectile spin-stabilization was considered together with the associated added-stress loads to projectile and launcher. In addition, both the design of the projectile configuration and materials capable of withstanding earth orbital, earth- and solar-system-escape launch loads, aerodynamic loads, and ablation and erosion penalties were studied. Projectile masses of ten to several hundred kilograms and launch speeds from 20 to 50 km/s are included in the analysis and discussion.

  8. Qualification of the 4th stage propulsor of the Brazilian launcher. SLV: A new sounding rocket

    NASA Astrophysics Data System (ADS)

    Boscov, Jayme; Toyama, Wilson Katsumi

    1989-06-01

    The development of the Satellite Launcher Vehicle (SLV) is presented. In particular, the attention is focused on the acquisition of the propulsion parameters of the 4th stage propulsor. The device feasibility analysis is considered. The system consists of a two staged sounding rocket. Its second stage contains the SVL, which can be launched by the 4th stage propulsor to a height range of about 50 to 60 km.

  9. Nano-Launcher Technologies, Approaches, and Life Cycle Assessment. Phase II

    NASA Technical Reports Server (NTRS)

    Zapata, Edgar

    2014-01-01

    Assist in understanding NASA technology and investment approaches, and other driving factors, necessary for enabling dedicated nano-launchers by industry at a cost and flight rate that (1) could support and be supported by an emerging nano-satellite market and (2) would benefit NASAs needs. Develop life-cycle cost, performance and other NASA analysis tools or models required to understand issues, drivers and challenges.

  10. Advanced Materials & Structural Concepts for Interstages Structues of Future Expendable Launchers

    NASA Astrophysics Data System (ADS)

    Diaz, V.; Cardone, T.; Ramusat, G.

    2014-06-01

    During the last 15 years, EADS CASA Espacio (ECE) has been leading the development of advanced composite structures for the Cryogenic Upper Stage of Ariane 5 launcher. In particular, ECE has developed, manufactured and qualified some of the most important structures of this Upper Stage like: Inter Stage Structure (ISS), Vehicle Equipment Bay (VEB), and several Payload Adaptor Systems (PAS).The next generation of expendable launchers will demand the use of advanced materials, high performance structural concepts, and cost-effective manufacturing processes in order to minimise the mass and cost of the cryogenic upper stage structures.In the frame of the Future Launcher Preparatory Programme (FLPP) promoted by ESA, some sub-scale demonstrators incorporating new materials, processes and structural concepts have been designed, analysed and tested in order to mature the most promising technologies. In particular, one of the sub-scale demonstrators developed in this programme, is representative of an Inter Stage Structure of a future expendable launcher. This demonstrator has incorporated the use of a new advanced composite material together with some advanced structural solutions for different parts of the structure:- monolithic skin reinforced with "Omega" stringers for the shell- an integrated CFRP ring for the lower I/FThis paper presents a summary of the performed work which includes:* A preliminary trade-off in order to select the optimum material and design concept* The analysis of the selected design* The basic characterization of the advanced selected material* The design, manufacturing and testing of some test articles representatives of the selected design solutions* Manufacturing trials for the selected structural concepts* Manufacturing and Testing of a subscale demonstrator of the ISS.

  11. Infantry Weapons Test Methodology Study. Volume 4. Grenade Launcher Test Methodology

    DTIC Science & Technology

    1972-04-01

    the window target; these data are fed into the computer contained data base manually . Any differences between competing weap- ons isolated by the time...procedures prescribed in the field manuals for standard launchers or rifle attachments, care must be taken to insure that pre- scribed methods and procedures...Under conditions where candidato weapons use different caliber projectiles, the irpact or signature of the projectile (shock wave, bullet strike

  12. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-05-25

    Cranes and rigging are being used to lift up the Core Stage Forward Skirt Umbilical (CSFSU) for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  13. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-05-25

    A construction worker welds a metal part during installation of the Core Stage Forward Skirt Umbilical on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  14. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-05-25

    Seeming to hang in midair, the Core Stage Forward Skirt Umbilical (CSFSU) is lifted high up by crane for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  15. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-05-25

    Construction workers assist as a crane lifts the Core Stage Forward Skirt Umbilical into position for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  16. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-05-25

    Construction workers assist as a crane lifts the Core Stage Forward Skirt Umbilical up for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  17. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-05-25

    Cranes and rigging are being used to lift the Core Stage Forward Skirt Umbilical (CSFSU) into position for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  18. Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

    NASA Image and Video Library

    2017-05-25

    A crane has been attached to the Core Stage Forward Skirt Umbilical (CSFSU) to lift it up for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

  19. Quantity Distance for the Kennedy Space Center Vehicle Assembly Building for Solid Propellant Fueled Launchers

    NASA Technical Reports Server (NTRS)

    Stover, Steven; Diebler, Corey; Frazier, Wayne

    2006-01-01

    The NASA KSC VAB was built to process Apollo launchers in the 1960's, and later adapted to process Space Shuttles. The VAB has served as a place to assemble solid rocket motors (5RM) and mate them to the vehicle's external fuel tank and Orbiter before rollout to the launch pad. As Space Shuttle is phased out, and new launchers are developed, the VAB may again be adapted to process these new launchers. Current launch vehicle designs call for continued and perhaps increased use of SRM segments; hence, the safe separation distances are in the process of being re-calculated. Cognizant NASA personnel and the solid rocket contractor have revisited the above VAB QD considerations and suggest that it may be revised to allow a greater number of motor segments within the VAB. This revision assumes that an inadvertent ignition of one SRM stack in its High Bay need not cause immediate and complete involvement of boosters that are part of a vehicle in adjacent High Bay. To support this assumption, NASA and contractor personnel proposed a strawman test approach for obtaining subscale data that may be used to develop phenomenological insight and to develop confidence in an analysis model for later use on full-scale situations. A team of subject matter experts in safety and siting of propellants and explosives were assembled to review the subscale test approach and provide options to NASA. Upon deliberations regarding the various options, the team arrived at some preliminary recommendations for NASA.

  20. Propulsive jet simulation with air and helium in launcher wake flows

    NASA Astrophysics Data System (ADS)

    Stephan, Sören; Radespiel, Rolf

    2016-12-01

    The influence on the turbulent wake of a generic space launcher model due to the presence of an under-expanded jet is investigated experimentally. Wake flow phenomena represent a significant source of uncertainties in the design of a space launcher. Especially critical are dynamic loads on the structure. The wake flow is investigated at supersonic (M=2.9 ) and hypersonic (M=5.9 ) flow regimes. The jet flow is simulated using air and helium as working gas. Due to the lower molar mass of helium, higher jet velocities are realized, and therefore, velocity ratios similar to space launchers can be simulated. The degree of under-expansion of the jet is moderate for the supersonic case (p_e/p_∞ ≈ 5 ) and high for the hypersonic case (p_e/p_∞ ≈ 90 ). The flow topology is described by Schlieren visualization and mean-pressure measurements. Unsteady pressure measurements are performed to describe the dynamic wake flow. The influences of the under-expanded jet and different jet velocities are reported. On the base fluctuations at a Strouhal number, around St_D ≈ 0.25 dominate for supersonic free-stream flows. With air jet, a fluctuation-level increase on the base is observed for Strouhal numbers above St_D ≈ 0.75 in hypersonic flow regime. With helium jet, distinct peaks at higher frequencies are found. This is attributed to the interactions of wake flow and jet.

  1. New Designs, Materials and Processes for Interstage Structures of Future Launchers

    NASA Astrophysics Data System (ADS)

    Mangas, C. B.; Diaz, V.

    2012-07-01

    Since the 1990’s EADS CASA Espacio has been leading the development of structures made out of advanced composite materials for the upper stage of Ariane 5: Inter Stage Structure (ISS), Vehicle Equipment Bay (VEB), different Payload Adaptor Systems, Satellite Dispensers and other structures. The next generation of launchers will demand an improvement on mechanical performances, reduction of mass and cost, and an optimization of the manufacturing processes. In the frame of the Future Launcher Preparatory Programme (FLPP) promoted by ESA, new designs, materials and processes are being studied and tested, in order to mature the most promising technologies and implement them in the future launchers. Specifically, in this programme these efforts are focused on different ISS structures. Taking as starting point the current ISS of Ariane 5 and IS3 of VEGA, new designs are suggested. Monocoque stiffened with omega stringers is the concept proposed for the ISS, while carbon fibre reinforced plastic (CFRP) - syntactic core sandwich is the one planned for IS3. This paper outlines the work performed in the programme: • Design and analysis of two Inter Stage Structures • Basic characterization tests for new materials: CFRP, syntactic core • Development tests at sample level for the different design solutions: different omega stringers, syncore sandwich • Manufacturing trials for the selected designs • Manufacturing of a sub-scaled demonstrator of the ISS

  2. Optimized use of superconducting magnetic energy storage for electromagnetic rail launcher powering

    NASA Astrophysics Data System (ADS)

    Badel, Arnaud; Tixador, Pascal; Arniet, Michel

    2012-01-01

    Electromagnetic rail launchers (EMRLs) require very high currents, from hundreds of kA to several MA. They are usually powered by capacitors. The use of superconducting magnetic energy storage (SMES) in the supply chain of an EMRL is investigated, as an energy buffer and as direct powering source. Simulations of direct powering are conducted to quantify the benefits of this method in terms of required primary energy. In order to enhance further the benefits of SMES powering, a novel integration concept is proposed, the superconducting self-supplied electromagnetic launcher (S3EL). In the S3EL, the SMES is used as a power supply for the EMRL but its coil serves also as an additional source of magnetic flux density, in order to increase the thrust (or reduce the required current for a given thrust). Optimization principles for this new concept are presented. Simulations based on the characteristics of an existing launcher demonstrate that the required current could be reduced by a factor of seven. Realizing such devices with HTS cables should be possible in the near future, especially if the S3EL concept is used in combination with the XRAM principle, allowing current multiplication.

  3. Propulsive jet simulation with air and helium in launcher wake flows

    NASA Astrophysics Data System (ADS)

    Stephan, Sören; Radespiel, Rolf

    2017-06-01

    The influence on the turbulent wake of a generic space launcher model due to the presence of an under-expanded jet is investigated experimentally. Wake flow phenomena represent a significant source of uncertainties in the design of a space launcher. Especially critical are dynamic loads on the structure. The wake flow is investigated at supersonic (M=2.9) and hypersonic (M=5.9) flow regimes. The jet flow is simulated using air and helium as working gas. Due to the lower molar mass of helium, higher jet velocities are realized, and therefore, velocity ratios similar to space launchers can be simulated. The degree of under-expansion of the jet is moderate for the supersonic case (p_e/p_∞ ≈ 5) and high for the hypersonic case (p_e/p_∞ ≈ 90). The flow topology is described by Schlieren visualization and mean-pressure measurements. Unsteady pressure measurements are performed to describe the dynamic wake flow. The influences of the under-expanded jet and different jet velocities are reported. On the base fluctuations at a Strouhal number, around St_D ≈ 0.25 dominate for supersonic free-stream flows. With air jet, a fluctuation-level increase on the base is observed for Strouhal numbers above St_D ≈ 0.75 in hypersonic flow regime. With helium jet, distinct peaks at higher frequencies are found. This is attributed to the interactions of wake flow and jet.

  4. Beam propagation and stray radiation in the ITER EC H&CD Upper Launcher

    NASA Astrophysics Data System (ADS)

    Platania, Paola; Bruschi, Alex; Farina, Daniela; Figini, Lorenzo; Goodman, Timothy; Krause, Alexandra; Henderson, Mark A.; Moro, Alessandro; Saibene, Gabriella; Toussaint, Matthieu; Sozzi, Carlo

    2015-03-01

    The four ITER Electron Cyclotron Upper Launchers (UL) are designed to control Magneto- Hydrodynamic instabilities with the deposition of Electron Cyclotron power. According to the present design, each launcher comprises two rows of four input waveguides, whose output beam is focused and driven towards the plasma by four sets of mirrors. In order to study the beam-launcher interaction throughout quasi-optical propagation, with particular attention to straylight behaviour, and to verify analytical calculations, a 3D model of the UL optical system has been implemented with the electromagnetic code GRASP® and the Physical Optics method. Detailed description of the components are introduced: pure hybrid mode HE11 from cylindrical waveguide as input beams, real shapes of the mirror contours, semi-analytical description of the ellipsoidal surfaces of focussing mirrors. A conceptual calculation scheme has been developed in order to take into account not only the direct contribution of the single source on its next scatterer but also the first order indirect effects: crosstalk from different lines of the same row and crosstalk from different rows have been evaluated after reflection on the first and third set of mirrors. The evaluations presented have been performed on the preliminary UL design, the last major milestone before finalization; however, the numerical model is suitable to be applied to future evolutions of the setup and/or other configurations.

  5. High Velocity Linear Induction Launcher with Exit-Edge Compensation for Testing of Aerospace Components

    NASA Technical Reports Server (NTRS)

    Kuznetsov, Stephen; Marriott, Darin

    2008-01-01

    Advances in ultra high speed linear induction electromagnetic launchers over the past decade have focused on magnetic compensation of the exit and entry-edge transient flux wave to produce efficient and compact linear electric machinery. The paper discusses two approaches to edge compensation in long-stator induction catapults with typical end speeds of 150 to 1,500 m/s. In classical linear induction machines, the exit-edge effect is manifest as two auxiliary traveling waves that produce a magnetic drag on the projectile and a loss of magnetic flux over the main surface of the machine. In the new design for the Stator Compensated Induction Machine (SCIM) high velocity launcher, the exit-edge effect is nulled by a dual wavelength machine or alternately the airgap flux is peaked at a location prior to the exit edge. A four (4) stage LIM catapult is presently being constructed for 180 m/s end speed operation using double-sided longitudinal flux machines. Advanced exit and entry edge compensation is being used to maximize system efficiency, and minimize stray heating of the reaction armature. Each stage will output approximately 60 kN of force and produce over 500 G s of acceleration on the armature. The advantage of this design is there is no ablation to the projectile and no sliding contacts, allowing repeated firing of the launcher without maintenance of any sort. The paper shows results of a parametric study for 500 m/s and 1,500 m/s linear induction launchers incorporating two of the latest compensation techniques for an air-core stator primary and an iron-core primary winding. Typical thrust densities for these machines are in the range of 150 kN/sq.m. to 225 kN/sq.m. and these compete favorably with permanent magnet linear synchronous machines. The operational advantages of the high speed SCIM launcher are shown by eliminating the need for pole-angle position sensors as would be required by synchronous systems. The stator power factor is also improved.

  6. Thermodynamic hardness and the maximum hardness principle

    NASA Astrophysics Data System (ADS)

    Franco-Pérez, Marco; Gázquez, José L.; Ayers, Paul W.; Vela, Alberto

    2017-08-01

    An alternative definition of hardness (called the thermodynamic hardness) within the grand canonical ensemble formalism is proposed in terms of the partial derivative of the electronic chemical potential with respect to the thermodynamic chemical potential of the reservoir, keeping the temperature and the external potential constant. This temperature dependent definition may be interpreted as a measure of the propensity of a system to go through a charge transfer process when it interacts with other species, and thus it keeps the philosophy of the original definition. When the derivative is expressed in terms of the three-state ensemble model, in the regime of low temperatures and up to temperatures of chemical interest, one finds that for zero fractional charge, the thermodynamic hardness is proportional to T-1(I -A ) , where I is the first ionization potential, A is the electron affinity, and T is the temperature. However, the thermodynamic hardness is nearly zero when the fractional charge is different from zero. Thus, through the present definition, one avoids the presence of the Dirac delta function. We show that the chemical hardness defined in this way provides meaningful and discernible information about the hardness properties of a chemical species exhibiting integer or a fractional average number of electrons, and this analysis allowed us to establish a link between the maximum possible value of the hardness here defined, with the minimum softness principle, showing that both principles are related to minimum fractional charge and maximum stability conditions.

  7. Thermodynamic hardness and the maximum hardness principle.

    PubMed

    Franco-Pérez, Marco; Gázquez, José L; Ayers, Paul W; Vela, Alberto

    2017-08-21

    An alternative definition of hardness (called the thermodynamic hardness) within the grand canonical ensemble formalism is proposed in terms of the partial derivative of the electronic chemical potential with respect to the thermodynamic chemical potential of the reservoir, keeping the temperature and the external potential constant. This temperature dependent definition may be interpreted as a measure of the propensity of a system to go through a charge transfer process when it interacts with other species, and thus it keeps the philosophy of the original definition. When the derivative is expressed in terms of the three-state ensemble model, in the regime of low temperatures and up to temperatures of chemical interest, one finds that for zero fractional charge, the thermodynamic hardness is proportional to T(-1)(I-A), where I is the first ionization potential, A is the electron affinity, and T is the temperature. However, the thermodynamic hardness is nearly zero when the fractional charge is different from zero. Thus, through the present definition, one avoids the presence of the Dirac delta function. We show that the chemical hardness defined in this way provides meaningful and discernible information about the hardness properties of a chemical species exhibiting integer or a fractional average number of electrons, and this analysis allowed us to establish a link between the maximum possible value of the hardness here defined, with the minimum softness principle, showing that both principles are related to minimum fractional charge and maximum stability conditions.

  8. Large Debris Dragging and De-Orbiting by the VEGA Launcher Using a Tether

    NASA Astrophysics Data System (ADS)

    Roux, Christophe; Federico, Martina; Gallucci, Stefano

    2013-08-01

    Thanks to limited adaptations - additional propellant tanks, addition of a small probe, few SW and Guidance, Navigation and Control (GNC) modifications - the launcher VEGA can be shown to be suited in terms of performances, safety and costs to a de-orbiting mission. Such a mission consists of three main phases: rendezvous, capture and de-orbiting. Focused on the last phase, this work presents the adaptation of GNC algorithms to realize the de-orbiting of a debris dragged by VEGA by means of a tether.

  9. Wound helium pressurant tank development for 2nd stage of Ariane 4 launcher

    NASA Astrophysics Data System (ADS)

    Valy, Y.; Coquet, P.

    1990-06-01

    The manufacture of a wound pressurant tank for the second stage of the Ariane 4 launcher is described. The goal of the manufacturing process is to save 26 kg per tank resulting in an overall savings of 78 kg for the second stage. This is equivalent to an extra mass payload of about 20 kg. The technical requirements of the tank are described. Development requirements and approach are outlined. Qualification standards of the design and qualification tests are described. Tank behavior is checked using acoustic emission and ultrasonic inspection.

  10. Comparison of the folded stripline and stacked stripline concepts to the folded waveguide launcher

    SciTech Connect

    Gardner, W.L.; Caughman, J.B.O.; Hoffman, D.J.; Probert, P.H.

    1993-12-31

    Two new concepts are being developed as possible upgrades to the folded waveguide launcher. The folded stripline is a folded waveguide with an additional conductor positioned inside. The term stripline refers to the resemblance of the design to microwave microstrip line. The conductor provides support for TEM mode propagation, which eliminates cutoff and the nonlinear frequency dependence of the waveguide impedance and phase velocity. A natural extension to the folded stripline is the stacked stripline, which comprises several stacked, independent TEM waveguides. Initial measurements indicate that both concepts have better magnetic flux coupling than the folded waveguide.

  11. Comparison of the folded stripline and stacked stripline concepts to the folded waveguide launcher

    SciTech Connect

    Gardner, W.L.; Caughman, J.B.O.; Hoffman, D.J. ); Probert, P.H. )

    1994-10-15

    Two new concepts are being developed as possible upgrades to the folded waveguide launcher. The folded stripline is a folded waveguide with an additional conductor positioned inside. The term [ital stripline] refers to the resemblance of the design to microwave microstrip line. The conductor provides support for TEM mode propagation, which eliminates cutoff and the nonlinear frequency dependence of the waveguide impedance and phase velocity. A natural extension to the folded stripline is the stacked stripline, which comprises several stacked, independent TEM waveguides. Initial measurements indicate that both concepts have better magnetic flux coupling than the folded waveguide.

  12. SAMP App Launcher: An On-Demand VO Application Starter by JMMC

    NASA Astrophysics Data System (ADS)

    Lafrasse, S.; Bourges, L.; Mella, G.

    2012-09-01

    SAMP is the dedicated Virtual Observatory protocol to ensure data exchange between compatible astronomical software running on personal computers. However, one SAMP weakness lies in its requirement to have interoperable applications already running in order to gracefully ensure communication between them. To circumvent this requirement, we present a dedicated application, plus some new SAMP specifications, focused on Java™ software available through the Java Web Start application-deployment technology (JNLP) at this stage. JMMC AppLauncher software fakes any described application by registering stub clients on the central SAMP hub. When one of the fake clients is solicited by any third-party software, AppLauncher takes the responsibility to start the true application, and then forwards the waiting SAMP message once fully started. To achieve this, we propose a set of new SAMP key-value pair to hold JNLP URLs. In the future, other kind of software packages technology could also be supported. We also want to standardize this solution, and get one central registry-like interoperable repository of compatible software, in order to open our mechanism to any third-party SAMP application provider. To illustrate, we briefly present our own use case, which demonstrates the need of such a tool for the JMMC applications suite.

  13. Aktiv De-Orbiting Onboard System from Leo of Upper Stages of Launchers

    NASA Astrophysics Data System (ADS)

    Trushlyakov, V.; Shalay, V.; Shatrov, J.; Jakovlev, M.; Kostantino, A.

    2009-03-01

    The active de-orbiting onboard system (VDOS) of upper separable parts (USP) stage of launchers from LEO into orbits of utilization with term of existence orbital lifetimes till 25 years is offered. ADOS it is based on use of power resources of not produced rests of liquid fuel onboard USP launchers with liquid propulsion module (LPM). Following systems enter in structure VDOS: the gas jet propulsion system consisting of a system of gasification, chambers of gas engines (GE), a control system. For gasification of the rests of liquid fuel the heat-carrier received in the autonomous gas generator is used. The gasification propellant components from each tank with temperature and the pressure determined by strength of the corresponding tank, move in chambers of the GE established on a top of a fuel compartment. After separation of a payload execute twist USP for preservation of its position in the space by activity of the GE. Ways of increase of a system effectiveness of gasification are offered by superposition on the entered heat-carrier of ultrasonic oscillations, and also introduction in gaseous fuel nanopowder of aluminum. The volume of adaptations of construction USP, connected with introduction VDOS does not exceed 5 % from weight of a dry construction.

  14. SHARP, a first step towards a full sized Jules Verne Launcher

    SciTech Connect

    Bertolini, L.R.; Hunter, J.W.; Powell, J.R.; Tidman, D.A.

    1993-05-01

    A vital element for space exploration and utilization is the ability to affordably place large quantities of consumables and building material into low earth orbit. Calculations and supportive data indicate this can be done with a large hydrogen gas gun referred to as the Jules Verne Launcher (JVL). We present a design for the JVL based upon the concept of side injecting preheated hydrogen along a long barrel. This dramatically reduces the peak pressures in the launcher as well as the pressures and g-loads at the vehicle. The JVL has the promise of reducing payload delivery costs to Low Earth Orbit (LEO) to below $500/kg. The Super High Altitude Research Project (SHARP) is a conventional two-stage hydrogen gas gun which is configured to launch 5 kg packages on suborbital trajectories. It is the first step towards the much larger Jules Verne system and will demonstrate several important features of the larger system. SHARP is currently in the middle of a series of tests aimed at its first milestone. This is to launch 5 kg at 4 km/sec horizontally. In its inclined configuration SHARP should launch vehicles to apogees in excess of 400 km and ranges in excess of 700 km.

  15. Recent advance on design and manufacturing of composite anisogrid structures for space launchers

    NASA Astrophysics Data System (ADS)

    Totaro, G.; De Nicola, F.

    2012-12-01

    Anisogrid composite shells have been developed and applied since the eighties by the Russian technology aiming at critical weight structures for space launchers, as interstages and cone adapters. The manufacturing process commonly applied is based on the wet filament winding. The paper concerns with some developments of design and manufacturing recently performed at the Italian Aerospace Research Center on a cylindrical structural model representative of this kind of structures. The framework of preliminary design is improved by introducing the concept of suboptimal configuration in order to match the stiffness requirement of the shell and minimise the mass, in conjunction with the typical strength constraints. The undertaken manufacturing process is based on dry robotic winding for the lattice structure and for the outer skin, with the aid of usual rubber tooling and new devices for the automated deposition strategy. Resin infusion under vacuum bag and co-cure of the system of ribs and skin is finally applied out-of-autoclave, with the aid of a heated mandrel. With such approach an interstage structural model (scale factor 1:1.5) has been designed, manufactured and tested. Design requirements and loads refer to a typical space launcher whose baseline configuration is made in aluminium. The global mechanical test of the manufactured structure has confirmed the expected high structural performance. The possibility to reach substantial weight savings in comparison with the aluminium benchmark has been fully demonstrated.

  16. Down-Bore Two-Laser Heterodyne Velocimetry of an Implosion-Driven Hypervelocity Launcher

    NASA Astrophysics Data System (ADS)

    Hildebrand, Myles; Huneault, Justin; Loiseau, Jason; Higgins, Andrew J.

    2015-06-01

    The implosion-driven launcher uses explosives to shock-compress helium, driving well-characterized projectiles to velocities exceeding 10 km/s. The masses of projectiles range between 0.1 - 10 g, and the design shows excellent scalability, reaching similar velocities across different projectile sizes. In the past, velocity measurements have been limited to muzzle velocity obtained via a high-speed videography upon the projectile exiting the launch tube. Recently, Photonic Doppler Velocimetry (PDV) has demonstrated the ability to continuously measure in-bore velocity, even in the presence of significant blow-by of high temperature helium propellant past the projectile. While a single-laser PDV is limited to approximately 8 km/s, a two-laser PDV system is developed that uses two lasers operating near 1550 nm to provide velocity measurement capabilities up to 16 km/s. The two laser PDV system is used to obtain a continuous velocity history of the projectile throughout the entire launch cycle. These continuous velocity data are used to validate models of the launcher cycle and compare different advanced concepts aimed at increasing the projectile velocity to well beyond 10 km/s.

  17. Fabrication issues and technology development for HELEOS (Hypervelocity Electromagnetic Launcher for Equation of State)

    SciTech Connect

    Susoeff, A.R.; Hawke, R.S.; Balk, J.K.; Hall, C.A.; McDonald, M.J.

    1988-02-01

    Starfire is a joint railgun project of Lawrence Livermore National Laboratory and Sandia National Laboratory and Sandia National Laboratory-Albuquerque. The goal of Starfire is to develop a Hypervelocity Electromagnetic Launcher for Equation of State (HELEOS) experiments. A two-stage light-gas gun is used as pre-injector. Each round-bore HELEOS railgun module is 12.7 mm in diameter and 2.4 m long. The muzzle end of the railgun is connected to a vacuum tank. Common materials and fabrication technology are used in the manufacture of all components,a nd modular design allows for extending the length of the railgun as progress dictates. The launcher uses a ''vee block'' geometry, which is designed to: provide compressive preload; operate with a 300-MPa (3-kbar) internal bore pressure; and easily accommodate interchangeable materials in the bore support structure and rail. We have performed full-scale material testing of the railgun and have developed a precision round-bore fabrication process. Air-gage inspection is used to determine bore diameter and straightness. We have also developed a surface mapping system to document the surface topography of the bore before and after an experiment. This paper presents fabrication details, results of tests conducted, and areas for potential improvement. 12 refs., 6 figs., 1 tab.

  18. Feasibility of an earth-to-space rail launcher system. [emphasizing nuclear waste disposal application

    NASA Technical Reports Server (NTRS)

    Rice, E. E.; Miller, L. A.; Marshall, R. A.; Kerslake, W. R.

    1982-01-01

    The feasibility of earth-to-space electromagnetic (railgun) launchers (ESRL) is considered, in order to determine their technical practicality and economic viability. The potential applications of the launcher include nuclear waste disposal into space, deep space probe launches, and atmospheric research. Examples of performance requirements of the ESRL system are a maximum acceleration of 10,000 g's for nuclear waste disposal in space (NWDS) missions and 2,500 g's for earth orbital missions, a 20 km/sec launch velocity for NWDS missions, and a launch azimuth of 90 degrees E. A brief configuration description is given, and test results indicate that for the 2020-2050 time period, as much as 3.0 MT per day of bulk material could be launched, and about 0.5 MT per day of high-level nuclear waste could be launched. For earth orbital missions, a significant projectile mass was approximately 6.5 MT, and an integral distributed energy store launch system demonstrated a good potential performance. ESRL prove to be economically and environmentally feasible, but an operational ESRL of the proposed size is not considered achievable before the year 2020.

  19. Millimeter wave experiment of ITER equatorial EC launcher mock-up

    SciTech Connect

    Takahashi, K.; Oda, Y.; Kajiwara, K.; Kobayashi, N.; Isozaki, M.; Sakamoto, K.; Omori, T.; Henderson, M.

    2014-02-12

    The full-scale mock-up of the equatorial launcher was fabricated in basis of the baseline design to investigate the mm-wave propagation properties of the launcher, the manufacturability, the cooling line management, how to assemble the components and so on. The mock-up consists of one of three mm-wave transmission sets and one of eight waveguide lines can deliver the mm-wave power. The mock-up was connected to the ITER compatible transmission line and the 170GHz gyrotron and the high power experiment was carried out. The measured radiation pattern of the beam at the location of 2.5m away from the EL mock-up shows the successful steering capability of 20°∼40°. It was also revealed that the radiated profile at both steering and fixed focusing mirror agreed with the calculation. The result also suggests that some unwanted modes are included in the radiated beam. Transmission of 0.5MW-0.4sec and of 0.12MW-50sec were also demonstrated.

  20. Feasibility of an earth-to-space rail launcher system. [emphasizing nuclear waste disposal application

    NASA Technical Reports Server (NTRS)

    Rice, E. E.; Miller, L. A.; Marshall, R. A.; Kerslake, W. R.

    1982-01-01

    The feasibility of earth-to-space electromagnetic (railgun) launchers (ESRL) is considered, in order to determine their technical practicality and economic viability. The potential applications of the launcher include nuclear waste disposal into space, deep space probe launches, and atmospheric research. Examples of performance requirements of the ESRL system are a maximum acceleration of 10,000 g's for nuclear waste disposal in space (NWDS) missions and 2,500 g's for earth orbital missions, a 20 km/sec launch velocity for NWDS missions, and a launch azimuth of 90 degrees E. A brief configuration description is given, and test results indicate that for the 2020-2050 time period, as much as 3.0 MT per day of bulk material could be launched, and about 0.5 MT per day of high-level nuclear waste could be launched. For earth orbital missions, a significant projectile mass was approximately 6.5 MT, and an integral distributed energy store launch system demonstrated a good potential performance. ESRL prove to be economically and environmentally feasible, but an operational ESRL of the proposed size is not considered achievable before the year 2020.

  1. Ordering of hard particles between hard walls

    NASA Astrophysics Data System (ADS)

    Chrzanowska, A.; Teixeira, P. I. C.; Ehrentraut, H.; Cleaver, D. J.

    2001-05-01

    The structure of a fluid of hard Gaussian overlap particles of elongation κ = 5, confined between two hard walls, has been calculated from density-functional theory and Monte Carlo simulations. By using the exact expression for the excluded volume kernel (Velasco E and Mederos L 1998 J. Chem. Phys. 109 2361) and solving the appropriate Euler-Lagrange equation entirely numerically, we have been able to extend our theoretical predictions into the nematic phase, which had up till now remained relatively unexplored due to the high computational cost. Simulation reveals a rich adsorption behaviour with increasing bulk density, which is described semi-quantitatively by the theory without any adjustable parameters.

  2. Use of the SIMBAD Gun Dynamics Code for Modelling the In-Bore Dynamics of EM Launchers

    DTIC Science & Technology

    2001-04-26

    launcher system. ACKNOWLEDGMENTS The authors wish to acknowledge the work of Mr D.N Bulman of Danby Engineering Ltd., Mr S.F. Storey of Simatics Ltd...and the firm of Temati Ltd. for their contribution to the work contained within this presentation. REFERENCES 1. SIMBAD Manual (Version 28). Danby

  3. University of Maryland-Republic Terrapin Sounding Rocket H121-2681-I(Terrapin) Model on the Launcher

    NASA Image and Video Library

    1956-10-21

    LAL 95,647 University of Maryland-Republic Terrapin sounding rocket mounted on special launcher, September 21, 1956. Photograph published in A New Dimension Wallops Island Flight Test Range: The First Fifteen Years by Joseph Shortal. A NASA publication. Page 506.

  4. Radar Cross-Section (RCS) Measurements of a Dismount With Rocket-Propelled Grenade (RPG) Launcher at Ka-Band

    DTIC Science & Technology

    2006-07-01

    corner reflector of known cross section was placed on the... Radar Cross - Section (RCS) Measurements of a Dismount with Rocket-Propelled Grenade (RPG) Launcher at Ka-Band by Suzanne R. Stratton and...Laboratory Aberdeen Proving Ground, MD 21005 ARL-TR-3855 July 2006 Radar Cross - Section (RCS) Measurements of a Dismount with

  5. Session: Hard Rock Penetration

    SciTech Connect

    Tennyson, George P. Jr.; Dunn, James C.; Drumheller, Douglas S.; Glowka, David A.; Lysne, Peter

    1992-01-01

    This session at the Geothermal Energy Program Review X: Geothermal Energy and the Utility Market consisted of five presentations: ''Hard Rock Penetration - Summary'' by George P. Tennyson, Jr.; ''Overview - Hard Rock Penetration'' by James C. Dunn; ''An Overview of Acoustic Telemetry'' by Douglas S. Drumheller; ''Lost Circulation Technology Development Status'' by David A. Glowka; ''Downhole Memory-Logging Tools'' by Peter Lysne.

  6. Hardness Tester for Polyur

    NASA Technical Reports Server (NTRS)

    Hauser, D. L.; Buras, D. F.; Corbin, J. M.

    1987-01-01

    Rubber-hardness tester modified for use on rigid polyurethane foam. Provides objective basis for evaluation of improvements in foam manufacturing and inspection. Typical acceptance criterion requires minimum hardness reading of 80 on modified tester. With adequate correlation tests, modified tester used to measure indirectly tensile and compressive strengths of foam.

  7. Hardness Tester for Polyur

    NASA Technical Reports Server (NTRS)

    Hauser, D. L.; Buras, D. F.; Corbin, J. M.

    1987-01-01

    Rubber-hardness tester modified for use on rigid polyurethane foam. Provides objective basis for evaluation of improvements in foam manufacturing and inspection. Typical acceptance criterion requires minimum hardness reading of 80 on modified tester. With adequate correlation tests, modified tester used to measure indirectly tensile and compressive strengths of foam.

  8. A socio-economic impact assessment of the European launcher sector

    NASA Astrophysics Data System (ADS)

    Monte, Luca del; Scatteia, Luigi

    2017-08-01

    In a context where the economic strains are challenging European policies as well as the very fabric of governmental contributions to public life, innovation and efficacy of public policy in research are called upon to support growth in Europe and to sustain employment and entrepreneurial capacities. Governments need evidence that the investments in space, while providing strategic tools to implement sovereign policies, create jobs and build the competitive European economy of the future. This is particularly true when the decisions at stake have a potential bearing on the future of the European space sector for at least the next 30 years, as it has been the case for the ESA Council at ministerial level meeting in December 2014. On that occasion, Ministers took the decision to start the development of a new Ariane 6 launcher and Vega evolutions having a critical bearing on the Member States' strategic industrial capabilities and on the sustainability of the European guaranteed access to space. Given the importance of the subject, and following similar studies undertaken in the past for e.g. the Ariane 1-4 programme, the Agency has requested an independent consulting team to perform a dedicated study to assess ex-post the direct, indirect and induced socio-economic impacts of the Ariane 5 programme (mid-term evaluation) and of the Vega programme (early evaluation) globally, at European level, and within the economies and industries of each ESA Member State. This paper presents the assessment of the socio-economic impacts allowing the evaluation of the return on public investments in launchers through ESA in a wider perspective, going beyond the purely economic terms. The scope of the assessment covered in total approximately 25 ESA programmatic and activity lines and 30,000 commitments from 1986 to end 2012. In the framework of the study, the economic impact of the European launcher programmes is measured through a GDP impact defined as the straight economic

  9. The hard metal diseases

    SciTech Connect

    Cugell, D.W. )

    1992-06-01

    Hard metal is a mixture of tungsten carbide and cobalt, to which small amounts of other metals may be added. It is widely used for industrial purposes whenever extreme hardness and high temperature resistance are needed, such as for cutting tools, oil well drilling bits, and jet engine exhaust ports. Cobalt is the component of hard metal that can be a health hazard. Respiratory diseases occur in workers exposed to cobalt--either in the production of hard metal, from machining hard metal parts, or from other sources. Adverse pulmonary reactions include asthma, hypersensitivity pneumonitis, and interstitial fibrosis. A peculiar, almost unique form of lung fibrosis, giant cell interstitial pneumonia, is closely linked with cobalt exposure.66 references.

  10. The hard metal diseases.

    PubMed

    Cugell, D W

    1992-06-01

    Hard metal is a mixture of tungsten carbide and cobalt, to which small amounts of other metals may be added. It is widely used for industrial purposes whenever extreme hardness and high temperature resistance are needed, such as for cutting tools, oil well drilling bits, and jet engine exhaust ports. Cobalt is the component of hard metal that can be a health hazard. Respiratory diseases occur in workers exposed to cobalt--either in the production of hard metal, from machining hard metal parts, or from other sources. Adverse pulmonary reactions include asthma, hypersensitivity pneumonitis, and interstitial fibrosis. A peculiar, almost unique form of lung fibrosis, giant cell interstitial pneumonia, is closely linked with cobalt exposure.

  11. Very High Specific Energy, Medium Power Li/CFx Primary Battery for Launchers and Space Probes

    NASA Astrophysics Data System (ADS)

    Brochard, Paul; Godillot, Gerome; Peres, Jean Paul; Corbin, Julien; Espinosa, Amaya

    2014-08-01

    Benchmark with existing technologies shows the advantages of the lithium-fluorinated carbon (Li/CFx) technology for use aboard future launchers in terms of a low Total Cost of Ownership (TCO), especially for high energy demanding missions such as re-ignitable upper stages for long GTO+ missions and probes for deep space exploration.This paper presents the new results obtained on this chemistry in terms of electrical and climatic performances, abuse tests and life tests. Studies - co-financed between CNES and Saft - looked at a pure CFx version with a specific energy up to 500 Wh/kg along with a medium power of 80 to 100 W/kg.

  12. Inverse synthetic aperture radar imagery of a man with a rocket propelled grenade launcher

    NASA Astrophysics Data System (ADS)

    Tran, Chi N.; Innocenti, Roberto; Kirose, Getachew; Ranney, Kenneth I.; Smith, Gregory

    2004-08-01

    As the Army moves toward more lightly armored Future Combat System (FCS) vehicles, enemy personnel will present an increasing threat to U.S. soldiers. In particular, they face a very real threat from adversaries using shoulder-launched, rocket propelled grenade (RPG). The Army Research Laboratory has utilized its Aberdeen Proving Ground (APG) turntable facility to collect very high resolution, fully polarimetric Ka band radar data at low depression angles of a man holding an RPG. In this paper, we examine the resulting low resolution and high resolution range profiles; and based on the observed radar cross section (RCS) value, we attempt to determine the utility of Ka band radar for detecting enemy personnel carrying RPG launchers.

  13. High temperature properties of alloys being considered for design of a concentric canister launcher

    SciTech Connect

    Kassner, M E; Lowry, R W; Rosen, R S

    1998-06-01

    This report describes a study to determine the high temperature mechanical properties of several titanium alloys and to compare them with properties of AISI 316L stainless steel and ASTM A 387 structural steel. The steel materials are less costly to procure but exhibit good resistance to corrosion in seawater environments. Six titanium alloys were evaluated as candidate materials for use in a c Concentric Canister Launcher (CCL). Each titanium alloy was tested at three temperatures (68°, 2000°F, and 2400°F). Strain-rate changes tests were used to determine the strain rate sensitivity of the alloys at each test temperature. Optical metallography was performed on two of the alloys to determine the relationship between test temperature and microstructure (presence of second phase precipitates, grain size). Complete test results are includes, a long with figures and tables of test data.

  14. Preliminary studies on the feasibility of a new concept for a Moon-to-Earth launcher

    NASA Astrophysics Data System (ADS)

    Migli, A.

    A new concept for a Moon launcher is presented. This launcher uses the working principles of a centrifugal sling, i.e. it is composed of a central pivotal element, a wire for launching the payload and a wire for a counterweight. Like the idea of a mass driver, which uses maglev technology, it is electrically powered; unlike the mass driver, which exploits linear acceleration for furnishing the escape speed needed, the payload gains velocity while payload wire and counterweight wire simultaneously deploy from the central pivotal element as its rotating speed increases. When exact speed and payload position are reached, a detachment system releases the payload. Wire length has been calculated to be in the order of 2 km; simple calcules on quasi-static conditions, that is with wire fully deployed and rotating at launching speed, indicate that a material like Kevlar 49 fibers for the wire would be able to sustain the centrifugal forces, and its mass would be around 100 kg. Given the wire length, launches can occur only tangentially to the ground. The payload nature would be lunar rock, preferably iron-rich volcanic glass, which seems to be easiest to be reduced and from which oxygen could be easily derived. Its mass, around 20 kg. A robot collector on the Moon's surface would be needed to search and select adequate payload and deliver it to the launcher. Target of the launch would be the Lagrange point L1, located between the Earth and the Moon. There, a catcher satellite would be needed to catch the payload and bring it to Earth orbit, where useful materials can be extracted from the lunar rock. My studies have mostly focused on space mechanics of the launch and demonstrated that an error of 10 milliseconds on the payload release time, or an error of 1 m/s on the evaluation of its speed, produce an error of about 60 km from target location. An optic control from the pivotal element can easily control this magnitude of errors. Absolute speed difference between the L1

  15. Beam masking to reduce cyclic error in beam launcher of interferometer

    NASA Technical Reports Server (NTRS)

    Ames, Lawrence L. (Inventor); Bell, Raymond Mark (Inventor); Dutta, Kalyan (Inventor)

    2005-01-01

    Embodiments of the present invention are directed to reducing cyclic error in the beam launcher of an interferometer. In one embodiment, an interferometry apparatus comprises a reference beam directed along a reference path, and a measurement beam spatially separated from the reference beam and being directed along a measurement path contacting a measurement object. The reference beam and the measurement beam have a single frequency. At least a portion of the reference beam and at least a portion of the measurement beam overlapping along a common path. One or more masks are disposed in the common path or in the reference path and the measurement path to spatially isolate the reference beam and the measurement beam from one another.

  16. Specifications and implementation of the RT MHD control system for the EC launcher of FTU

    NASA Astrophysics Data System (ADS)

    Galperti, C.; Alessi, E.; Boncagni, L.; Bruschi, A.; Granucci, G.; Grosso, A.; Iannone, F.; Marchetto, C.; Nowak, S.; Panella, M.; Sozzi, C.; Tilia, B.

    2012-09-01

    To perform real time plasma control experiments using EC heating waves by using the new fast launcher installed on FTU a dedicated data acquisition and elaboration system has been designed recently. A prototypical version of the acquisition/control system has been recently developed and will be tested on FTU machine in its next experimental campaign. The open-source framework MARTe (Multi-threaded Application Real-Time executor) on Linux/RTAI real-time operating system has been chosen as software platform to realize the control system. Standard open-architecture industrial PCs, based either on VME bus and CompactPCI bus equipped with standard input/output cards are the chosen hardware platform.

  17. In-bore diagnostic and modeling of an electrothermal plasma launcher

    SciTech Connect

    Hurley, J.D.

    1993-01-01

    A diagnostic method has been developed to measure the high heat flux produced in the electrothermal plasma launcher SIRENS. The method involves attaching a thermocouple to the back surface of a target to obtain the temperature history of the back surface, which is a direct indication of the heat flux incident on the front surface. The measured temperature history is an input to a developed one dimensional (1-D), time dependent heat conduction code which uses the temperature history of the back surface to determine the incident heat flux on the front surface of the target. A one dimensional time dependent code, ODIN, was developed to model the plasma formation and flow in electrothermal launchers. ODIN models the plasma formation and flow into the source section and the plasma expansion into and through the barrel section. ODIN models the energy transport, particle transport, plasma resistivity, plasma viscosity, and equation-of-state. The source and barrel sections were broken into a specific number of cells and each cell was considered to be in local thermodynamic equilibrium (LTE), with the plasma modeled as a viscous fluid. The primary objective of the numerical simulation was to predict the time and axial variation of the plasma flow and to predict the magnitude of the drag forces acting on the plasma. SIRENS has been operated at atmospheric conditions using a fuse placed between the two electrodes in the source section to initiate the discharge. Three different types of fuses were tested, with the best results obtaining using a thin triangular shaped aluminum fuse. SIRENS has also be used to launch projectiles, with projectile masses ranging from 400 mg to 1500 mg. The maximum velocity obtained was 1.74 km/sec at an input energy of 2.5 kJ, using a 540 mg Lexan projectile with an efficiency of 33%.

  18. In-Bore Diagnostic and Modeling of AN Electrothermal Plasma Launcher

    NASA Astrophysics Data System (ADS)

    Hurley, Jeffery Dale

    A diagnostic method has been developed to measure the high heat flux produced in the electrothermal plasma launcher SIRENS. The method involves attaching a thermocouple to the back surface of a target to obtain the temperature history of the back surface, which is a direct indication of the heat flux incident on the front surface. The measured temperature history is an input to a developed one dimensional (1-D), time dependent heat conduction code which uses the temperature history of the back surface to determine the incident heat flux on the front surface of the target. A one dimensional time dependent code, ODIN, was developed to model the plasma formation and flow in electrothermal launchers. ODIN models the plasma formation and flow in the source section and the plasma expansion into and through the barrel section. ODIN models the energy transport, particle transport, plasma resistivity, plasma viscosity, and equation-of-state. The source and barrel sections were broken into a specific number of cells and each cell was considered to be in local thermodynamic equilibrium (LTE), with the plasma modeled as a viscous fluid. The primary objective of the numerical simulation was to predict the time and axial variation of the plasma flow and to predict the magnitude of the drag forces acting on the plasma. SIRENS has been operated at atmospheric conditions using a fuse placed between the two electrodes in the source section to initiate the discharge. Three different types of fuses were tested, with the best results obtained using a thin triangular shaped aluminum fuse. SIRENS has also been used to launch projectiles, with projectile masses ranging from 400 mg to 1500 mg. The maximum velocity obtained was 1.74 km/sec at an input energy of 2.5 kJ, using a 540 mg Lexan projectile with an efficiency of 33%.

  19. ESC-B: The Cryogenic Upper Stage for Europe's Heavy Lift Launcher Ariane 5ECB

    NASA Astrophysics Data System (ADS)

    Juhls, A.

    2002-01-01

    -A. Juhls, Astrium GmbH -M. Lepelletier, Snecma Moteurs -JM. Bahu, CNES -C. Poincheval, CNES. In the year 1998 the European ministerial council decided to initiate the Ariane 5 Plus programme in order to upgrade the European heavy lift launcher Ariane 5. The market was changing more rapidly than predicted showing steadily growing satellite mass and the demand for flexible missions while strong competitors were intensifying their preparations to enter the commercial business. The answer was to improve the Ariane 5 launcher by modifying the cryogenic first (or lower ?) stage and the solid boosters and by introducing two cryogenic upper stages in two steps: In order to cope with the short term need of a significant growth of GTO lift capacity up to 10 t the first denoted ESC-A shall enter commercial service in 2002. Four years later a more powerful second version shall take over enabling a GTO performance of 12 t and providing versatile mission capability. The paper will focus on this new cryogenic upper stage denoted ESC-B giving first a general description of main characteristics and constituents. The article will highlight different challenging aspects of the ESC-B development: Ambitious economical conditions regarding both limited development budgets and the strong need to reduce production cost require improved working methods and an adjustment of the conventional development logic, in particular regarding new verification methods. Furthermore Europe is now facing the complex combination of versatile mission capability together with a powerful cryogenic upper stage. The paper will present the approach to define reasonable mission scenarios in order to cover customer demands while avoiding too stringent system requirements. Along with VINCI, Europe's first expander cycle type engine featuring an extendable nozzle dedicated subsystems will be described which allow 4 re-ignitions and 6 hours of ballistic flight. The paper concludes with the summary of the

  20. Electromagnetic launcher studies of breakup and aerosol formation in molten uranium alloy

    SciTech Connect

    Benson, D.A.; Rader, D.J.

    1990-03-01

    An understanding of dispersal of nuclear materials from an explosive event is needed to support design studies of weapon storage and transportation. Assessing the consequences and requirements for cleanup of a fire or nonnuclear detonation of a system containing nuclear material requires knowledge of the aerosol formation process. Information about the aerosol chemical composition, the physical size and shape of the particulates, as well as the efficiency of aerosol formation ate needed to conduct meaningful assessments. This report describes laboratory tests to study aerosol from materials of interest. An electromagnetic launcher is used to heat and propel molten metallic samples under energetic high-velocity conditions. We describe the apparatus and first results from tests using uranium-molybdenum alloy samples. Contained laboratory-scale measurements are described that determine aerosol morphology, chemical composition, and aerosol formation efficiency under high-velocity conditions. Data from the launcher tests describe (1) the aerodynamic breakup process of high-velocity molten liquid into droplets, and (2) the formation of still finer aerosols by combustion of these droplets at high velocity. The measurements show efficient aerosol production in air that is dominated by the formation of fine chain-agglomerate combustion aerosol. Particle morphology information for both the chain agglomerate and the less common liquid breakup products is described. The aerodynamic breakup of the liquid sample material is described. Lognormal distributions are shown to accurately represent the data. The geometric mean diameter is related to the mass mean diameter and maximum stable droplet diameter for the distributions. 28 refs., 27 figs., 3 tabs.

  1. Dynamic hardness of metals

    NASA Astrophysics Data System (ADS)

    Liang, Xuecheng

    Dynamic hardness (Pd) of 22 different pure metals and alloys having a wide range of elastic modulus, static hardness, and crystal structure were measured in a gas pulse system. The indentation contact diameter with an indenting sphere and the radius (r2) of curvature of the indentation were determined by the curve fitting of the indentation profile data. r 2 measured by the profilometer was compared with that calculated from Hertz equation in both dynamic and static conditions. The results indicated that the curvature change due to elastic recovery after unloading is approximately proportional to the parameters predicted by Hertz equation. However, r 2 is less than the radius of indenting sphere in many cases which is contradictory to Hertz analysis. This discrepancy is believed due to the difference between Hertzian and actual stress distributions underneath the indentation. Factors which influence indentation elastic recovery were also discussed. It was found that Tabor dynamic hardness formula always gives a lower value than that directly from dynamic hardness definition DeltaE/V because of errors mainly from Tabor's rebound equation and the assumption that dynamic hardness at the beginning of rebound process (Pr) is equal to kinetic energy change of an impact sphere over the formed crater volume (Pd) in the derivation process for Tabor's dynamic hardness formula. Experimental results also suggested that dynamic to static hardness ratio of a material is primarily determined by its crystal structure and static hardness. The effects of strain rate and temperature rise on this ratio were discussed. A vacuum rotating arm apparatus was built to measure Pd at 70, 127, and 381 mum sphere sizes, these results exhibited that Pd is highly depended on the sphere size due to the strain rate effects. P d was also used to substitute for static hardness to correlate with abrasion and erosion resistance of metals and alloys. The particle size effects observed in erosion were

  2. Organizing Your Hard Disk.

    ERIC Educational Resources Information Center

    Stocker, H. Robert; Hilton, Thomas S. E.

    1991-01-01

    Suggests strategies that make hard disk organization easy and efficient, such as making, changing, and removing directories; grouping files by subject; naming files effectively; backing up efficiently; and using PATH. (JOW)

  3. Organizing Your Hard Disk.

    ERIC Educational Resources Information Center

    Stocker, H. Robert; Hilton, Thomas S. E.

    1991-01-01

    Suggests strategies that make hard disk organization easy and efficient, such as making, changing, and removing directories; grouping files by subject; naming files effectively; backing up efficiently; and using PATH. (JOW)

  4. Radiation from hard objects

    SciTech Connect

    Canavan, G.H.

    1997-02-01

    The inference of the diameter of hard objects is insensitive to radiation efficiency. Deductions of radiation efficiency from observations are very sensitive - possibly overly so. Inferences of the initial velocity and trajectory vary similarly, and hence are comparably sensitive.

  5. Mobile Learning Using Mobile Phones

    ERIC Educational Resources Information Center

    Vicente, Paula

    2013-01-01

    The participation in mobile learning programs is conditioned by having/using mobile communication technology. Those who do not have or use such technology cannot participate in mobile learning programs. This study evaluates who are the most likely participants of mobile learning programs by examining the demographic profile and mobile phone usage…

  6. Analysis of near-surface flow physics in a two-stage, 10 km/s, electromagnetic launcher

    SciTech Connect

    Buckingham, A.C.; Hawke, R.S.

    1990-06-06

    This is a report of progress in the analysis of several apparently influential physical processes observed in current electromagnetic launcher performance experiments. Boundary layer and thin-film Couette flow processes in the hypervelocity range (approaching 10 km/s) are the focus of this work. The specific launch device under study has a two-stage acceleration: initially a light gas projectile injection phase followed by a plasma driven Lorentz force acceleration phase. Our emphasis is on understanding the concomitant influence of plasma transport, gas phase and gas/solid kinetics, skin depth, solid neutral and ionic particle seed additives on near-wall boundary layer and Couette flow processes. Studies are initiated on the effects of plasma-enriching ion additives and wall transpiration cooling with respect to increasing the integrity, performance, and launch-to-launch endurance of this type of electromagnetic launcher (EML). 14 refs., 8 figs.

  7. European Space Agency's launcher multibody dynamics simulator used for system and subsystem level analyses

    NASA Astrophysics Data System (ADS)

    Baldesi, Gianluigi; Toso, Mario

    2012-06-01

    software (such as NASTRAN, CATIA, MATLAB/Simulink, etc.), it is possible to reproduce in detail most of the key subsystems and disciplines (such as trajectory, structures, configuration, mechanisms, aerodynamics, propulsion, GNC, propulsion, etc.) of the launcher in a single simulation. The simulator has been also tuned in order to be used in the studies on new launch vehicle feasibility concepts performed at ESA's Concurrent Design Facility. Furthermore, the code has been adjusted to tackle specific events, such as multi-payload separation dynamics (Swarm, Galileo, etc.), thrust vector control subsystem studies (such as GSTP3, GSTP4, Vega), lift-off analysis (such as Vega, etc.), general loads (Vega, etc.). In this paper, an overview of the launcher multibody dynamics simulator capabilities is presented by illustrating some examples.

  8. Softeners for hardness removal.

    PubMed

    Shetty, Rashma; Manjunath, N T; Babu, B T Suresh

    2005-10-01

    The depletion of water resources, both surface and subsurface and deterioration of water quality made researchers and policy makers to think of the possible remedies to make water sources potable / wholesome. There is a need to address the problems of hardness and fluoride in subsurface water on priority basis. In this direction, bench scale studies were conducted to evaluate the performance of water softeners. Indepth studies were carried out at University B.D.T College of Engineering, Davangere, Karnataka, to assess the performance of bench scale softeners of D to H ratio 1:2, 1:3, 1:4 in removing hardness of varied concentrations from both synthetic and natural water samples. Studies revealed that irrespective of D to H ratio of softeners, the waters having hardness concentration up to 1000 mg/l can be treated to the same degree (81.68% and above). The findings of regeneration studies and cost economics are also summarized in this paper.

  9. Probing the plasma near high power wave launchers in fusion devices for static and dynamic electric fields (invited)

    SciTech Connect

    Klepper, C. C. Isler, R. C.; Biewer, T. M.; Caughman, J. B.; Green, D. L.; Harris, J. H.; Hillis, D. L.; Martin, E. H.; Colas, L.; Goniche, M.; Hillairet, J.; Panayotis, S.; Pegourié, B.; Jacquot, J.; Lotte, Ph.; Colledani, G.; Ekedahl, A.; Litaudon, X.; Shannon, S. C.

    2014-11-15

    An exploratory study was carried out in the long-pulse tokamak Tore Supra, to determine if electric fields in the plasma around high-power, RF wave launchers could be measured with non-intrusive, passive, optical emission spectroscopy. The focus was in particular on the use of the external electric field Stark effect. The feasibility was found to be strongly dependent on the spatial extent of the electric fields and overlap between regions of strong (>∼1 kV/cm) electric fields and regions of plasma particle recycling and plasma-induced, spectral line emission. Most amenable to the measurement was the RF electric field in edge plasma, in front of a lower hybrid heating and current drive launcher. Electric field strengths and direction, derived from fitting the acquired spectra to a model including time-dependent Stark effect and the tokamak-range magnetic field Zeeman-effect, were found to be in good agreement with full-wave modeling of the observed launcher.

  10. Probing the plasma near high power wave launchers in fusion devices for static and dynamic electric fields (invited).

    PubMed

    Klepper, C C; Martin, E H; Isler, R C; Colas, L; Goniche, M; Hillairet, J; Panayotis, S; Pegourié, B; Jacquot, J; Lotte, Ph; Colledani, G; Biewer, T M; Caughman, J B; Ekedahl, A; Green, D L; Harris, J H; Hillis, D L; Shannon, S C; Litaudon, X

    2014-11-01

    An exploratory study was carried out in the long-pulse tokamak Tore Supra, to determine if electric fields in the plasma around high-power, RF wave launchers could be measured with non-intrusive, passive, optical emission spectroscopy. The focus was in particular on the use of the external electric field Stark effect. The feasibility was found to be strongly dependent on the spatial extent of the electric fields and overlap between regions of strong (>∼1 kV/cm) electric fields and regions of plasma particle recycling and plasma-induced, spectral line emission. Most amenable to the measurement was the RF electric field in edge plasma, in front of a lower hybrid heating and current drive launcher. Electric field strengths and direction, derived from fitting the acquired spectra to a model including time-dependent Stark effect and the tokamak-range magnetic field Zeeman-effect, were found to be in good agreement with full-wave modeling of the observed launcher.

  11. Spacecraft configuration study for second generation mobile satellite system

    NASA Technical Reports Server (NTRS)

    Louie, M.; Vonstentzsch, W.; Zanella, F.; Hayes, R.; Mcgovern, F.; Tyner, R.

    1985-01-01

    A high power, high performance communicatons satellite bus being developed is designed to satisfy a broad range of multimission payload requirements in a cost effective manner and is compatible with both STS and expendable launchers. Results are presented of tradeoff studies conducted to optimize the second generation mobile satellite system for its mass, power, and physical size. Investigations of the 20-meter antenna configuration, transponder linearization techniques, needed spacecraft modifications, and spacecraft power, dissipation, mass, and physical size indicate that the advanced spacecraft bus is capable of supporting the required payload for the satellite.

  12. Measurement Uncertainty Analysis of an Accelerometer Calibration Using a POC Electromagnetic Launcher

    SciTech Connect

    Timpson, Erik J.; Engel, T. G.

    2012-06-12

    A pulse forming network (PFN), helical electromagnetic launcher (HEML), command module (CM), and calibration table (CT) were built and evaluated for the combined ability to calibrate an accelerometer. The PFN has a maximum stored nergy of 19.25 kJ bank and is fired by a silicon controlled rectifier (SCR), with appropriate safety precautions. The HEML is constructed out of G-10 fiberglass reinforced epoxy and is designed to accelerate a mass of 600 grams to a velocity of 10 meters per second. The CM is microcontroller-based running Arduino Software. The CM has a keypad input and 7 segment outputs of the PFN voltage and desired charging voltage. After entering a desired PFN voltage, the CM controls the charging of the PFN. When the two voltages are equal it sends a pulse to the SCR to fire the PFN and in turn, the HEML. The HEML projectile’s tip hits a target that is held by the CT. The CT consists of a table to hold the PFN and HEML, a vacuum chuck, air bearing, velocimeter and catch pot. The target is held with the vacuum chuck awaiting impact. After impact, the air bearing allows the target to fall freely so that the velocimeter can accurately read. A known acceleration is determined from the known change in velocity of the target. Thus, if an accelerometer was attached to the target, the measured value can be compared to the known value.

  13. Development of a high-velocity free-flight launcher : the Ames light-gas gun

    NASA Technical Reports Server (NTRS)

    Charters, A C; Denardo, B Pat; Rossow, Vernon J

    1955-01-01

    Recent interest in long-range missiles has stimulated a search for new experimental techniques which can reproduce in the laboratory the high temperatures and Mach numbers associated with the missiles' flight. One promising possibility lies in free-flight testing of laboratory models which are flown at the full velocity of the missile. In this type of test, temperatures are approximated and aerodynamic heating of the model is representative of that experienced by the missile in high-velocity flight. A prime requirement of the free-flight test technique is a device which had the capacity for launching models at the velocities desired. In response to thie need, a gun firing light models at velocities up to 15,000 feet per second has been developed at the Ames Aeronautical Laboratory. The design of this gun, the analysis of its performance, and the results of the initial firing trials are described in this paper. The firing trials showed that the measured velocities and pressures agreed well with the predicted values. Also, the erosion of the launch tube was very small for the eleven rounds fired. The performance of the gun suggests that it will prove to be a satisfactory launcher for high-velocity free-flight tests. However, it should be mentioned that only the gross performance has been evaluated so far, and, consequently, the operation of the gun must be investigated in further detail before its performance can be reliably predicted over its full operating range.

  14. A PLANAR, RECTANGULAR WAVEGUIDE LAUNCHER AND EXTRACTOR FOR A DUAL-MODED RF POWER DISTRIBUTION SYSTEM

    SciTech Connect

    Nantista, Christopher D.

    2000-11-21

    The desire to reduce the amount of low-loss, circular-waveguide delay line required in a pulse-compressing power distribution system for the Next Linear Collider has led to the pursuit of multi-moded schemes [1]. In such a system, power is delivered to different destinations through the same waveguide via different propagating modes. Current plans [2] utilize two modes, with manipulations done primarily in overmoded rectangular guide. We describe two key components of the system, a four-input/four-output, dual-mode launcher and an extractor for diverting one mode from the delay line to an accelerator feed while allowing the other to pass on to an upstream feed. These novel passive waveguide devices utilize the rectangular TE10 and TE20 modes. Because they must carry up to 600 MW pulsed rf power, H-planar symmetry is maintained in their designs to allow the use of overheight waveguide, and features that invite breakdown, such as coupling slots, irises, and septa, are avoided. Special rectangular-to-circular tapers [3] will be used to convert between the above modes and the circular TE11{sup o} (TE12{sup o}) and TE01{sup o} delay line modes, respectively. Rectangular waveguide for relative ease of handling. Mode converters, including special cross-section tapers [3] will be used to transform between the above circular waveguide modes and the TE20 and TE10 rectangular waveguide modes, respectively.

  15. Cryogenic pellet launcher adapted for controlling of tokamak plasma edge instabilities.

    PubMed

    Lang, P T; Cierpka, P; Harhausen, J; Neuhauser, J; Wittmann, C; Gál, K; Kálvin, S; Kocsis, G; Sárközi, J; Szepesi, T; Dorner, C; Kauke, G

    2007-02-01

    One of the main challenges posed recently on pellet launcher systems in fusion-oriented plasma physics is the control of the plasma edge region. Strong energy bursts ejected from the plasma due to edge localized modes (ELMs) can form a severe threat for in-vessel components but can be mitigated by sufficiently frequent triggering of the underlying instabilities using hydrogen isotope pellet injection. However, pellet injection systems developed mainly for the task of ELM control, keeping the unwanted pellet fueling minimized, are still missing. Here, we report on a novel system developed under the premise of its suitability for control and mitigation of plasma edge instabilities. The system is based on the blower gun principle and is capable of combining high repetition rates up to 143 Hz with low pellet velocities. Thus, the flexibility of the accessible injection geometry can be maximized and the pellet size kept low. As a result the new system allows for an enhancement in the tokamak operation as well as for more sophisticated experiments investigating the underlying physics of the plasma edge instabilities. This article reports on the design of the new system, its main operational characteristics as determined in extensive test bed runs, and also its first test at the tokamak experiment ASDEX Upgrade.

  16. Guidelines for internal optics optimization of the ITER EC H and CD upper launcher

    SciTech Connect

    Moro, A.; Bruschi, A.; Figini, L.; Farina, D.; Platania, P.; Sozzi, C.; Chavan, R.; Goodman, T. P.; Krause, A.; Landis, J. D.; Sanchez Galan, F.; Toussaint, M.; Henderson, M. A.; Saibene, G.

    2014-02-12

    The importance of localized injection of Electron Cyclotron waves to control Magneto-HydroDynamic instability is well assessed in tokamak physics and the set of four Electron Cyclotron (EC) Upper Launchers (UL) in ITER is mainly designed for this purpose. Each of the 4 ULs uses quasi-optical mirrors (shaping and planes, fixed and steerable) to redirect and focus 8 beams (in two rows, with power close to 1 MW per beam coming from the EC transmission lines) in the plasma region where the instability appears. Small beam dimensions and maximum beam superposition guarantee the necessary localization of the driven current. To achieve the goal of MHD stabilization with minimum EC power to preserve the energy confinement in the outer half of the plasma cross section, optimization of the quasi-optical design is required and a guideline of a strategy is presented. As a result of this process and following the guidelines indicated, modifications of the design (new mirrors positions, rotation axes and/or focal properties) will be proposed for the next step of an iterative process, including the mandatory compatibility check with the mechanical constraints.

  17. A new HyperVelocity Launcher (HVL) for space science application

    SciTech Connect

    Chhabildas, L.C.

    1991-12-31

    Very high driving pressures (tens or hundreds of GPa), are required to accelerate flier plats to hypervelocities. This loading pressure pulse on the fiber plates must be nearly shockless to prevent the plate from melting or vaporizing. This is accomplished by using graded-density impactors referred to as ``pillows.`` When this graded-density material is used to impact a flier-plate in a modified two-stage light gas gun, nearly shockless megabar pressures are introduced into the flier plate. The pressure pulses must also be tailored to prevent spallation of the flier-plate. This technique has been used to launch nominally 1-mm-thick aluminum, magnesium and titanium (gram-size) intact plates to 10.4 km/s, and 0.5-mm-thick aluminum and titanium (half-gram size) intact plates to 12.2 km/s. This is the highest mass-velocity capability attained with laboratory launchers to data, and should open up new regimes of impact physics and lethality studies related to space sciences for laboratory investigations. 14 refs.

  18. A new HyperVelocity Launcher (HVL) for space science application

    SciTech Connect

    Chhabildas, L.C.

    1991-01-01

    Very high driving pressures (tens or hundreds of GPa), are required to accelerate flier plats to hypervelocities. This loading pressure pulse on the fiber plates must be nearly shockless to prevent the plate from melting or vaporizing. This is accomplished by using graded-density impactors referred to as pillows.'' When this graded-density material is used to impact a flier-plate in a modified two-stage light gas gun, nearly shockless megabar pressures are introduced into the flier plate. The pressure pulses must also be tailored to prevent spallation of the flier-plate. This technique has been used to launch nominally 1-mm-thick aluminum, magnesium and titanium (gram-size) intact plates to 10.4 km/s, and 0.5-mm-thick aluminum and titanium (half-gram size) intact plates to 12.2 km/s. This is the highest mass-velocity capability attained with laboratory launchers to data, and should open up new regimes of impact physics and lethality studies related to space sciences for laboratory investigations. 14 refs.

  19. Numerical investigation of the near wake of generic space launcher systems at transonic and supersonic flows

    NASA Astrophysics Data System (ADS)

    Statnikov, V.; Glatzer, C.; Meiß, J.-H.; Meinke, M.; Schröder, W.

    2013-06-01

    Numerical simulations of the near wake of generic rocket configurations are performed at transonic and supersonic freestream conditions to improve the understanding of the highly intricate near wake structures. The Reynolds number in both flow regimes is 106 based on the main body diameter, i. e., specific freestream conditions of ESA's Ariane launcher trajectory. The geometry matches models used in experiments in the framework of the German Transregional Collaborative Research Center TRR40. Both axisymmetric wind tunnel models possess cylindrical sting supports, representing a nozzle to allow investigations of a less disturbed wake flow. A zonal approach consisting of a Reynolds averaged Navier-Stokes (RANS) and a large-eddy simulation (LES) is applied. It is shown that the highly unsteady transonic wake flow at Ma∞ = 0.7 is characterized by the expanding separated shear layer, while the Mach 6.0 wake is defined by a shock, expansion waves, and a recompression region. In both cases, an instantaneous view on the base characteristics reveals complex azimuthal flow structures even for axisymmetric geometries. The flow regimes are discussed by comparing the aerodynamic characteristics, such as the size of the recirculation region and the turbulent kinetic energy.

  20. Update on Progress of Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS) - Cyclops

    NASA Technical Reports Server (NTRS)

    Newswander, Daniel; Smith, James P.; Lamb, Craig R.; Ballard, Perry G.

    2014-01-01

    The Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS), known as "Cyclops" to the International Space Station (ISS) community, was introduced last August (2013) during Technical Session V: From Earth to Orbit of the 27th Annual AIAA/USU Conference on Small Satellites. Cyclops is a collaboration between the NASA ISS Program, NASA Johnson Space Center Engineering, and Department of Defense (DoD) Space Test Program (STP) communities to develop a dedicated 50-100 kg class ISS small satellite deployment system. This paper will address the progress of Cyclops through its fabrication, assembly, flight certification, and on-orbit demonstration phases. It will also go into more detail regarding its anatomy, its satellite deployment concept of operations, and its satellite interfaces and requirements. Cyclops is manifested to fly on Space-X 4 which is currently scheduled in July 2014 with its initial satellite deployment demonstration of DoD STP's SpinSat and UT/TAMU's Lonestar satellites being late summer or fall of 2014.

  1. A crude model to study radio frequency induced density modification close to launchers

    SciTech Connect

    Van Eester, Dirk; Crombé, Kristel

    2015-12-15

    The interplay between radio frequency (RF) waves and the density is discussed by adopting the general framework of a 2-time-scale multi-fluid treatment, allowing to separate the dynamics on the RF time scale from that on the time scale on which macroscopic density and flows vary as a result of the presence of electromagnetic and/or electrostatic fields. The focus is on regions close to launchers where charge neutrality is incomplete and waves are commonly evanescent. The fast time scale dynamics influences the slow time scale behavior via quasilinear terms (the Ponderomotive force for the case of the equation of motion). Electrons and ions are treated on the same footing. Also, both fast and slow waves are retained in the wave description. Although this work is meant as a subtopic of a large study—the wave induced “convective cell” physics at hand is of a 2- or 3-dimensional nature while this paper limits itself to a single dimension—a few tentative examples are presented.

  2. Experimental Investigation Of Base Flow Buffeting On The Ariane 5 Launcher Using High Speed PIV

    NASA Astrophysics Data System (ADS)

    Schrijer, F. F. J.; Sciacchitano, A.; Scarrano, F.; Hannemann, K.; Pallegoix, J.-F.; Maseand, J. E. J.; Schwane, R.

    2011-05-01

    Experiments have been performed on a 1:60 scale Ariane 5 launcher in the DNW HST wind tunnel by means of two-component particle image velocimetry (2C-PIV). Measurements are performed for Mach 0.5 and Mach 0.8. The investigation focuses on studying the flow-buffeting phenomenon in the base of an Ariane V rocket. In total four configurations are tested: reference configuration, skirt, scoop and reference configuration without struts. It has been found that the presence of the struts has a large effect on the flow field; the secondary flow caused by the struts decreases the separated region and increases the overall turbulence. The skirt has the effect that the shear layer separates later and therefore does not reattach on the nozzle. Also in the separated region a secondary recirculation region is formed. For the scoop configuration it was observed that a second wake was formed by the scoop element causing the overall shear layer to become thicker. Finally using POD analysis two dominant modes are identified that can be associated to the separation bubble and shear layer dynamics.

  3. The Aquarius, A Proposal for a Nano-Satellite Launcher Vehicle

    NASA Astrophysics Data System (ADS)

    Calero, J. S.

    Here we present a nano launcher vehicle capable of injecting a 14 kg satellite in a polar orbit of 400 kilometres of altitude. This vehicle, which we call Aquarius, has an approximate mass of 1,000 kg and is transported and launched as an external load from a fighter aircraft such as the F-18 Hornet or EF-2000 Typhoon. Although we are dealing with a theoretical exercise, the solution we propose here is totally realistic. The calculation methods employed are the usual ones in the preliminary phases of projects of this type, and the technology proposed for the systems corresponds to current state-of-the- art. Of course there are some areas in which conjecture was introduced as to study them in detail would take too long; however we have tried to provide solutions that are both realistic and likely. As regards the numerical values employed in the diverse parameters and magnitudes, we tended to be a bit more conservative. Conceptual aspects, calculation methods, technological solutions and economic and scheduling provisions all derive from knowledge acquired from the extinct Capricornio programme.

  4. A new technology for production of high thickness carbon/carbon composites for launchers application

    NASA Astrophysics Data System (ADS)

    Albano, Marta; Delfini, Andrea; Pastore, Roberto; Micheli, Davide; Marchetti, Mario

    2016-11-01

    Carbon-Carbon (C/C) composites are known for their extraordinary stability and excellent mechanical properties, almost unchanged at high temperatures. Among the several advanced applications, C/C based materials can be used in engines as nozzle throat section for launchers. In particular, the main feature for such employment is the material high resistance in extreme thermal environment. On the other hand, large-size items are required for this kind of purposes, thus introducing criticalities in terms of material uniformity and final overall properties. Up to now, there no standard for the production of high thickness C/C structures. In this paper a novel manufacturing method is analyzed, following each phase of the process, from the carbon fiber preform design and preparation to the carbon densification by chemical vapor infiltration method. Five preforms of large dimensions with different characteristics have been manufactured and infiltrated. The realized prototypes have been then analyzed by means of mechanical, physical and morphological tests. Aim of the results of this preliminary work is to establish a set of guidelines for a well-defined high thickness C/C production method.

  5. Down-bore two-laser heterodyne velocimetry of an implosion-driven hypervelocity launcher

    NASA Astrophysics Data System (ADS)

    Hildebrand, Myles; Huneault, Justin; Loiseau, Jason; Higgins, Andrew J.

    2017-01-01

    The implosion-driven launcher uses explosives to shock-compress helium, driving well-characterized projectiles to velocities exceeding 10 km/s. The masses of projectiles range between 0.1 - 15 g, and the design shows excellent scalability, reaching similar velocities across different projectile sizes. In the past, velocity measurements have been limited to muzzle velocity obtained via a high-speed videography upon the projectile exiting the launch tube. Recently, Photon Doppler Velocimetry (PDV) has demonstrated the ability to continuously measure in-bore velocity, even in the presence of significant blow-by of high temperature helium propellant past the projectile. While a single laser system sampled at 40 GS/s with a 13 GHz detector/scope bandwidth is limited to 8 km/s, a two-laser PDV system is developed that uses two lasers operating near 1550 nm to provide velocity measurement capabilities up to 16 km/s with the same bandwidth and sampling rate. The two-laser PDV system is used to obtain a continuous velocity history of the projectile throughout the entire launch cycle. These internal ballistics trajectories are used to compare different advanced concepts aimed at increasing the projectile velocity to well beyond 10 km/s.

  6. Mobility management in mobile IP

    NASA Astrophysics Data System (ADS)

    Medidi, Sirisha; Golshani, Forouzan

    2002-07-01

    There is an emerging interest in integrating mobile wireless communication with the Internet based on the Ipv6 technology. Many issues introduced by the mobility of users arise when such an integration is attempted. This paper addresses the problem of mobility management, i.e., that of tracking the current IP addresses of mobile terminals and sustaining active IP connections as mobiles move. The paper presents some architectural and mobility management options for integrating wireless access to the Internet. We then present performance results for Mobile IPv4, route optimization and Mobile IPv6.

  7. Budgeting in Hard Times.

    ERIC Educational Resources Information Center

    Parrino, Frank M.

    2003-01-01

    Interviews with school board members and administrators produced a list of suggestions for balancing a budget in hard times. Among these are changing calendars and schedules to reduce heating and cooling costs; sharing personnel; rescheduling some extracurricular activities; and forming cooperative agreements with other districts. (MLF)

  8. Budgeting in Hard Times.

    ERIC Educational Resources Information Center

    Parrino, Frank M.

    2003-01-01

    Interviews with school board members and administrators produced a list of suggestions for balancing a budget in hard times. Among these are changing calendars and schedules to reduce heating and cooling costs; sharing personnel; rescheduling some extracurricular activities; and forming cooperative agreements with other districts. (MLF)

  9. Running in Hard Times

    ERIC Educational Resources Information Center

    Berry, John N., III

    2009-01-01

    Roberta Stevens and Kent Oliver are campaigning hard for the presidency of the American Library Association (ALA). Stevens is outreach projects and partnerships officer at the Library of Congress. Oliver is executive director of the Stark County District Library in Canton, Ohio. They have debated, discussed, and posted web sites, Facebook pages,…

  10. Running in Hard Times

    ERIC Educational Resources Information Center

    Berry, John N., III

    2009-01-01

    Roberta Stevens and Kent Oliver are campaigning hard for the presidency of the American Library Association (ALA). Stevens is outreach projects and partnerships officer at the Library of Congress. Oliver is executive director of the Stark County District Library in Canton, Ohio. They have debated, discussed, and posted web sites, Facebook pages,…

  11. CSI: Hard Drive

    ERIC Educational Resources Information Center

    Sturgeon, Julie

    2008-01-01

    Acting on information from students who reported seeing a classmate looking at inappropriate material on a school computer, school officials used forensics software to plunge the depths of the PC's hard drive, searching for evidence of improper activity. Images were found in a deleted Internet Explorer cache as well as deleted file space.…

  12. Recruiting Hard-to-Reach Subjects for Exercise Interventions: A Multi-Centre and Multi-Stage Approach Targeting General Practitioners and Their Community-Dwelling and Mobility-Limited Patients

    PubMed Central

    Brach, Michael; Moschny, Anna; Bücker, Bettina; Klaaßen-Mielke, Renate; Trampisch, Matthias; Wilm, Stefan; Platen, Petra; Hinrichs, Timo

    2013-01-01

    The general practitioner (GP)’s practice appears to be an ideal venue for recruiting community-dwelling older adults with limited mobility. This study (Current Controlled Trials ISRCTN17727272) aimed at evaluating the recruiting process used for a multi-centre exercise intervention (HOMEfit). Each of six steps resulted in an absolute number of patients (N1–N6). Sex and age (for N4–N6) and reasons for dropping out were assessed. Patient database screening (N1–N3) at 15 GP practices yielded N1 = 5,990 patients aged 70 and above who had visited their GP within the past 6 months, N2 = 5,467 after exclusion of institutionalised patients, N3 = 1,545 patients eligible. Using a pre-defined limitation algorithm in order to conserve the practices’ resources resulted in N4 = 1,214 patients (80.3 ± 5.6 years, 68% female), who were then officially invited to the final assessment of eligibility at the GP’s practice. N5 = 434 patients (79.5 ± 5.4 years, 69% female) attended the practice screening (n = 13 of whom had not received an official invitation). Finally, N6 = 209 (79.8 ± 5.2 years, 74% female) were randomised after they were judged eligible and had given their written informed consent to participate in the randomised controlled trial (overall recruitment rate: 4.4%). The general strategy of utilising a GP’s practice to recruit the target group proved beneficial. The data and experiences presented here can help planners of future exercise-intervention studies. PMID:24317380

  13. KENNEDY SPACE CENTER, FLA. - United Space Alliance (USA) workers J.D. Wise, left, and Robert Shackelford, with drill, try to stop an approximately 24-foot-long crack from getting any bigger on the Mobile Launcher Platform (MLP), which is holding the Space Shuttle Discovery en route to Launch Pad 39A for the STS-82 mission. Discovery was on its way out to the launch pad when engineers heard a loud bang and noticed that a crack had developed on the MLP. Rollout had begun shortly after 7 a.m. EST and was stopped at about 8:25 a.m. This Y-shaped crack is on the MLP surface and runs from near the left-hand solid rocket booster flame hole toward the near corner of the MLP. Rollout of Discovery resumed just past noon after structural engineers determined that the integrity of the MLP had not been compromised. Discovery is scheduled to lift off on the second Hubble Space Telescope servicing mission on Feb. 11.

    NASA Image and Video Library

    1997-01-17

    KENNEDY SPACE CENTER, FLA. - United Space Alliance (USA) workers J.D. Wise, left, and Robert Shackelford, with drill, try to stop an approximately 24-foot-long crack from getting any bigger on the Mobile Launcher Platform (MLP), which is holding the Space Shuttle Discovery en route to Launch Pad 39A for the STS-82 mission. Discovery was on its way out to the launch pad when engineers heard a loud bang and noticed that a crack had developed on the MLP. Rollout had begun shortly after 7 a.m. EST and was stopped at about 8:25 a.m. This Y-shaped crack is on the MLP surface and runs from near the left-hand solid rocket booster flame hole toward the near corner of the MLP. Rollout of Discovery resumed just past noon after structural engineers determined that the integrity of the MLP had not been compromised. Discovery is scheduled to lift off on the second Hubble Space Telescope servicing mission on Feb. 11.

  14. Unemployment: Hard-Core or Hard-Shell?

    ERIC Educational Resources Information Center

    Lauer, Robert H.

    1972-01-01

    The term hard-core'' makes the unemployed culpable; the term hard shell'' shifts the burden to the employer, and the evidence from the suburban plant indicates that a substantial part of the problem must lie there. (DM)

  15. Super-Hard Superconductivity

    NASA Astrophysics Data System (ADS)

    Adams, Philip; Prozorov, Ruslan

    2005-03-01

    We present the magnetic response of Type-II superconductivity in the extreme pinning limit, where screening currents within an order of magnitude of the Ginzburg-Landau depairing critical current density develop upon the application of a magnetic field. We show that this ``super-hard'' limit is well approximated in highly disordered, cold drawn, Nb wire whose magnetization response is characterized by a cascade of Meissner-like phases, each terminated by a catastrophic collapse of the magnetization. Direct magneto-optic measurements of the flux penetration depth in the virgin magnetization branch are in excellent agreement with the exponential model in which Jc(B)=Jco(-B/Bo), where Jco˜5x10^6 A/cm^2 for Nb. The implications for the fundamental limiting hardness of a superconductor will be discussed.

  16. Wave induced density modification in RF sheaths and close to wave launchers

    NASA Astrophysics Data System (ADS)

    Van Eester, D.; Crombé, K.; Lu, Ling-Feng

    2015-12-01

    With the return to full metal walls - a necessary step towards viable fusion machines - and due to the high power densities of current-day ICRH (Ion Cyclotron Resonance Heating) or RF (radio frequency) antennas, there is ample renewed interest in exploring the reasons for wave-induced sputtering and formation of hot spots. Moreover, there is experimental evidence on various machines that RF waves influence the density profile close to the wave launchers so that waves indirectly influence their own coupling efficiency. The present study presents a return to first principles and describes the wave-particle interaction using a 2-time scale model involving the equation of motion, the continuity equation and the wave equation on each of the time scales. Through the changing density pattern, the fast time scale dynamics is affected by the slow time scale events. In turn, the slow time scale density and flows are modified by the presence of the RF waves through quasilinear terms. Although finite zero order flows are identified, the usual cold plasma dielectric tensor - ignoring such flows - is adopted as a first approximation to describe the wave response to the RF driver. The resulting set of equations is composed of linear and nonlinear equations and is tackled in 1D in the present paper. Whereas the former can be solved using standard numerical techniques, the latter require special handling. At the price of multiple iterations, a simple 'derivative switch-on' procedure allows to reformulate the nonlinear problem as a sequence of linear problems. Analytical expressions allow a first crude assessment - revealing that the ponderomotive potential plays a role similar to that of the electrostatic potential arising from charge separation - but numerical implementation is required to get a feeling of the full dynamics. A few tentative examples are provided to illustrate the phenomena involved.

  17. Combined experimental and numerical investigation of a transonic space launcher wake

    NASA Astrophysics Data System (ADS)

    Scharnowski, S.; Statnikov, V.; Meinke, M.; Schröder, W.; Kähler, C. J.

    2015-06-01

    Combined experimental und numerical investigations of the turbulent wake of a generic space launcher at transonic free stream conditions (Ma∞ = 0.7 and ReD = 1.0 · 106) are performed to gain a better understanding of intricate phenomena of the wake flow physics and to validate new methods for its analysis. The experiments are conducted at the Bundeswehr University Munich using a high-repetition-rate particle image velocimetry (PIV) system, while the numerical investigation is performed by the Institute of Aerodynamics of RWTH Aachen University using a zonal Reynolds-averaged Navier-Stokes (RANS) / large-eddy simulation (LES) approach. After a characterization of the wake flow topology, two applied methodologies are compared to each other with respect to the spatial and temporal resolution stressing their strengths and shortcomings. It is shown that both methods are well suitable for the prediction of the mean and instantaneous values of the turbulent velocity field, whereas for a reliable statistical analysis of the velocity fluctuations, the PIV approach is more appropriate due to the computational time limitations of the LES. On the other hand, the high spatial and temporal resolution of the LES allows for an accurate detection of relevant coherent structures as well as tracking their motion in time without any significant artificial vortex agglomeration that can be critical in the case of PIV. Furthermore, the influence of different model assumptions, e. g., the level of incoming turbulence and model vibrations, is discussed in order to emphasize the importance of a side-by-side combination of both investigation techniques.

  18. Structures, Material and Processes Technology in the Future Launchers Preparatory Program

    NASA Astrophysics Data System (ADS)

    Baiocco, P.; Ramusat, G.; Breteau, J.; Bouilly, Th.; Lavelle, Fl.; Cardone, T.; Fischer, H.; Appel, S.; Block, U.

    2014-06-01

    In the frame of the technology / demonstration activity for European launchers developments and evolutions, a top-down / bottom-up approach has been employed to identify promising technologies and alternative conception. The top-down approach consists in looking for system-driven design solutions and the bottom-up approach features design solutions leading to substantial advantages for the system. The main investigations have been devoted to structures, material and process technology.Preliminary specifications have been used in order to permit sub-system design with the goal to find the major benefit for the overall launch system. In this respect competitiveness factors have been defined to down- select the technology and the corresponding optimized design. The development cost, non-recurring cost, industrialization and operational aspects have been considered for the identification of the most interesting solutions. The TRL/IRL has been assessed depending on the manufacturing company and a preliminary development plan has been issued for some technology.The reference launch systems for the technology and demonstration programs are mainly Ariane 6 with its evolutions, VEGA C/E and others possible longer term systems. Requirements and reference structures architectures have been considered in order to state requirements for representative subscale or full scale demonstrators. The major sub-systems and structures analyzed are for instance the upper stage structures, the engine thrust frame (ETF), the inter stage structures (ISS), the cryogenic propellant tanks, the feeding lines and their attachments, the pressurization systems, the payload adapters and fairings. A specific analysis has been devoted to the efficiency of production processes associated to technologies and design features.The paper provides an overview of the main results of the technology and demonstration activities with the associated system benefits. The materials used for the main structures are

  19. Wave induced density modification in RF sheaths and close to wave launchers

    SciTech Connect

    Van Eester, D.; Lu, Ling-Feng

    2015-12-10

    With the return to full metal walls - a necessary step towards viable fusion machines - and due to the high power densities of current-day ICRH (Ion Cyclotron Resonance Heating) or RF (radio frequency) antennas, there is ample renewed interest in exploring the reasons for wave-induced sputtering and formation of hot spots. Moreover, there is experimental evidence on various machines that RF waves influence the density profile close to the wave launchers so that waves indirectly influence their own coupling efficiency. The present study presents a return to first principles and describes the wave-particle interaction using a 2-time scale model involving the equation of motion, the continuity equation and the wave equation on each of the time scales. Through the changing density pattern, the fast time scale dynamics is affected by the slow time scale events. In turn, the slow time scale density and flows are modified by the presence of the RF waves through quasilinear terms. Although finite zero order flows are identified, the usual cold plasma dielectric tensor - ignoring such flows - is adopted as a first approximation to describe the wave response to the RF driver. The resulting set of equations is composed of linear and nonlinear equations and is tackled in 1D in the present paper. Whereas the former can be solved using standard numerical techniques, the latter require special handling. At the price of multiple iterations, a simple ’derivative switch-on’ procedure allows to reformulate the nonlinear problem as a sequence of linear problems. Analytical expressions allow a first crude assessment - revealing that the ponderomotive potential plays a role similar to that of the electrostatic potential arising from charge separation - but numerical implementation is required to get a feeling of the full dynamics. A few tentative examples are provided to illustrate the phenomena involved.

  20. Investigations on the turbulent wake of a generic space launcher geometry in the hypersonic flow regime

    NASA Astrophysics Data System (ADS)

    Saile, D.; Gülhan, A.; Henckels, A.; Glatzer, C.; Statnikov, V.; Meinke, M.

    2013-06-01

    The turbulent wake flow of generic rocket configurations is investigated experimentally and numerically at a freestream Mach number of 6.0 and a unit Reynolds number of 10·106 m-1. The flow condition is based on the trajectory of Ariane V-like launcher at an altitude of 50 km, which is used as the baseline to address the overarching tasks of wake flows in the hypersonic regime like fluid-structural coupling, reverse hot jets and base heating. Experimental results using pressure transducers and the high-speed Schlieren measurement technique are shown to gain insight into the local pressure fluctuations on the base and the oscillations of the recompression shock. This experimental configuration features a wedgeprofiled strut orthogonally mounted to the main body. Additionally, the influence of cylindrical dummy nozzles attached to the base of the rocket is investigated, which is the link to the numerical investigations. Here, the axisymmetric model possesses a cylindrical sting support of the same diameter as the dummy nozzles. The sting support allows investigations for an undisturbed wake flow. A time-accurate zonal Reynolds-Averaged Navier-Stokes/Large Eddy Simulation (RANS/LES) approach is applied to identify shocks, expansion waves, and the highly unsteady recompression region numerically. Subsequently, experimental and numerical results in the strut-averted region are compared with regard to the wall pressure and recompression shock frequency spectra. For the compared configurations, experimental pressure spectra exhibit dominant Strouhal numbers at about SrD = 0.03 and 0.27, and the recompression shock oscillates at 0.2. In general, the pressure and recompression shock fluctuations numerically calculated agree reasonably with the experimental results. The experiments with a blunt base reveal base-pressure spectra with dominant Strouhal numbers at 0.08 at the center position and 0.145, 0.21-0.22, and 0.31-0.33 at the outskirts of the base.

  1. Periodically kicked hard oscillators.

    PubMed

    Cecchi, G. A.; Gonzalez, D. L.; Magnasco, M. O.; Mindlin, G. B.; Piro, O.; Santillan, A. J.

    1993-01-01

    A model of a hard oscillator with analytic solution is presented. Its behavior under periodic kicking, for which a closed form stroboscopic map can be obtained, is studied. It is shown that the general structure of such an oscillator includes four distinct regions; the outer two regions correspond to very small or very large amplitude of the external force and match the corresponding regions in soft oscillators (invertible degree one and degree zero circle maps, respectively). There are two new regions for intermediate amplitude of the forcing. Region 3 corresponds to moderate high forcing, and is intrinsic to hard oscillators; it is characterized by discontinuous circle maps with a flat segment. Region 2 (low moderate forcing) has a certain resemblance to a similar region in soft oscillators (noninvertible degree one circle maps); however, the limit set of the dynamics in this region is not a circle, but a branched manifold, obtained as the tangent union of a circle and an interval; the topological structure of this object is generated by the finite size of the repelling set, and is therefore also intrinsic to hard oscillators.

  2. SUPER HARD SURFACED POLYMERS

    SciTech Connect

    Mansur, Louis K; Bhattacharya, R; Blau, Peter Julian; Clemons, Art; Eberle, Cliff; Evans, H B; Janke, Christopher James; Jolly, Brian C; Lee, E H; Leonard, Keith J; Trejo, Rosa M; Rivard, John D

    2010-01-01

    High energy ion beam surface treatments were applied to a selected group of polymers. Of the six materials in the present study, four were thermoplastics (polycarbonate, polyethylene, polyethylene terephthalate, and polystyrene) and two were thermosets (epoxy and polyimide). The particular epoxy evaluated in this work is one of the resins used in formulating fiber reinforced composites for military helicopter blades. Measures of mechanical properties of the near surface regions were obtained by nanoindentation hardness and pin on disk wear. Attempts were also made to measure erosion resistance by particle impact. All materials were hardness tested. Pristine materials were very soft, having values in the range of approximately 0.1 to 0.5 GPa. Ion beam treatment increased hardness by up to 50 times compared to untreated materials. For reference, all materials were hardened to values higher than those typical of stainless steels. Wear tests were carried out on three of the materials, PET, PI and epoxy. On the ion beam treated epoxy no wear could be detected, whereas the untreated material showed significant wear.

  3. Investigation of battery-charged-capacitor pulsed-power systems for electromagnetic-launcher experiments. Final report, Jan 90-Apr 91

    SciTech Connect

    Cornette, J.B.

    1992-02-01

    Candidate pulsed power systems for electromagnetic launchers constitute two broad categories: rotating machinery and non-rotating devices. Rotating machinery for this purpose is under development at several industrial and educational institutions around the world. Non-rotating hardware includes capacitors, batteries, and inductors. These, too, are the subject of research programs, but as yet, are much larger than rotating supplies of equal power and energy capability. In 1988, system studies identified several attractive pulsed power systems for electromagnetic launchers. Battery charged capacitor pulsed power systems were among those identified as promising for electromagnetic launcher systems. The basic equations governing the battery charging capacitor sequence, and the capacitor discharge into an electromagnetic launcher are the subject of this report. A battery charged capacitor system powering an electromagnetic launcher has also been built and tested. This experiment not only validates the system concept with presently available hardware, but can be used to establish a baseline for evaluation of future systems when technology in capacitor and battery power and energy densities improve.

  4. Staking Tool for Hard Metals

    NASA Technical Reports Server (NTRS)

    Stein, J. A.

    1982-01-01

    Simple tool stakes hard-steel parts--that is, forces one part into recess on another, deforming receiving part so that it restrains inserted one. Tool allows small machine shops to stake hard steel without massive presses. Can be used, for example, to insert ball and spring into hard steel snap-tool body such as that used to turn socket wrenches. Use is not limited to hard steel; can be used as well to assemble parts made of softer materials.

  5. Hard metal composition

    DOEpatents

    Sheinberg, Haskell

    1986-01-01

    A composition of matter having a Rockwell A hardness of at least 85 is formed from a precursor mixture comprising between 3 and 10 weight percent boron carbide and the remainder a metal mixture comprising from 70 to 90 percent tungsten or molybdenum, with the remainder of the metal mixture comprising nickel and iron or a mixture thereof. The composition has a relatively low density of between 7 to 14 g/cc. The precursor is preferably hot pressed to yield a composition having greater than 100% of theoretical density.

  6. Hard metal composition

    DOEpatents

    Sheinberg, H.

    1983-07-26

    A composition of matter having a Rockwell A hardness of at least 85 is formed from a precursor mixture comprising between 3 and 10 wt % boron carbide and the remainder a metal mixture comprising from 70 to 90% tungsten or molybdenum, with the remainder of the metal mixture comprising nickel and iron or a mixture thereof. The composition has a relatively low density of between 7 and 14 g/cc. The precursor is preferably hot pressed to yield a composition having greater than 100% of theoretical density.

  7. Revisiting the definition of local hardness and hardness kernel.

    PubMed

    Polanco-Ramírez, Carlos A; Franco-Pérez, Marco; Carmona-Espíndola, Javier; Gázquez, José L; Ayers, Paul W

    2017-05-17

    An analysis of the hardness kernel and local hardness is performed to propose new definitions for these quantities that follow a similar pattern to the one that characterizes the quantities associated with softness, that is, we have derived new definitions for which the integral of the hardness kernel over the whole space of one of the variables leads to local hardness, and the integral of local hardness over the whole space leads to global hardness. A basic aspect of the present approach is that global hardness keeps its identity as the second derivative of energy with respect to the number of electrons. Local hardness thus obtained depends on the first and second derivatives of energy and electron density with respect to the number of electrons. When these derivatives are approximated by a smooth quadratic interpolation of energy, the expression for local hardness reduces to the one intuitively proposed by Meneses, Tiznado, Contreras and Fuentealba. However, when one combines the first directional derivatives with smooth second derivatives one finds additional terms that allow one to differentiate local hardness for electrophilic attack from the one for nucleophilic attack. Numerical results related to electrophilic attacks on substituted pyridines, substituted benzenes and substituted ethenes are presented to show the overall performance of the new definition.

  8. Steady-State Cycle Deck Launcher Developed for Numerical Propulsion System Simulation

    NASA Technical Reports Server (NTRS)

    VanDrei, Donald E.

    1997-01-01

    industry and NASA. The NPSS Steady-State Cycle Deck team released a batch version of the Steady-State Cycle Deck in March 1996. Version 1.1 was released in June 1996. During fiscal 1997, NPSS accepted enhancements and modifications to the Steady-State Cycle Deck launcher. Consistent with NPSS' commercialization plan, these modifications will be done by a third party that can provide long-term software support.

  9. Final Progress Report for the NASA Inductrack Model Rocket Launcher at the Lawrence Livermore National Laboratory

    SciTech Connect

    Tung, L S; Post, R F; Martinez-Frias, J

    2001-06-27

    The Inductrack magnetic levitation system, developed at the Lawrence Livermore National Laboratory, was studied for its possible use for launching rockets. Under NASA sponsorship, a small model system was constructed at the Laboratory to pursue key technical aspects of this proposed application. The Inductrack is a passive magnetic levitation system employing special arrays of high-field permanent magnets (Halbach arrays) on the levitating cradle, moving above a ''track'' consisting of a close-packed array of shorted coils with which are interleaved with special drive coils. Halbach arrays produce a strong spatially periodic magnetic field on the front surface of the arrays, while canceling the field on their back surface. Relative motion between the Halbach arrays and the track coils induces currents in those coils. These currents levitate the cradle by interacting with the horizontal component of the magnetic field. Pulsed currents in the drive coils, synchronized with the motion of the carrier, interact with the vertical component of the magnetic field to provide acceleration forces. Motional stability, including resistance to both vertical and lateral aerodynamic forces, is provided by having Halbach arrays that interact with both the upper and the lower sides of the track coils. At present, a 7.8 meter track composed of drive and levitation coils has been built and the electronic drive circuitry performs as designed. A 9 kg cradle that carries the Halbach array of permanent magnets has been built. A mechanical launcher is nearly complete which will provide an initial cradle velocity of 9 m/s into the electronic drive section. We have found that the drag forces from the levitation coils were higher than in our original design. However, measurements of drag force at velocities less than 1 m/s are exactly as predicted by theory. Provided here are recommended design changes to improve the track's performance so that a final velocity of 40 m/s can be achieved with

  10. Experimental and numerical investigation of the turbulent wake flow of a generic space launcher configuration

    NASA Astrophysics Data System (ADS)

    Statnikov, V.; Saile, D.; Meiß, J.-H.; Henckels, A.; Meinke, M.; Gülhan, A.; Schröder, W.

    2015-06-01

    The turbulent wake of a generic space launcher at cold hypersonic freestream conditions is investigated experimentally and numerically to gain detailed insight into the intricate base flow phenomena of space vehicles at upper stages of the flight trajectory. The experiments are done at Ma∞ = 6 and ReD = 1.7 · 106 m-1 by the German Aerospace Center (DLR) and the corresponding computations are performed by the Institute of Aerodynamics Aachen using a zonal Reynolds-averaged Navier-Stokes / Large-Eddy Simulation (RANS/LES) approach. Two different aft-body geometries consisting of a blunt base and an attached cylindrical nozzle dummy are considered. It is found that the wind tunnel model support attached to the upper side of the main body has a nonnegligible impact on the wake along the whole circumference, albeit on the opposite side, the effects are minimal compared to an axisymmetric configuration. In the blunt-base case, the turbulent supersonic boundary layer undergoes a strong aftexpansion on the model shoulder leading to the formation of a confined low-pressure (p/p∞ ≈ 0.2) recirculation region. Adding a nozzle dummy causes the shear layer to reattach on the its wall at x/D ˜ 0.6 and the base pressure level to increase (p/p∞ ≈ 0.25) compared to the blunt-base case. For both configurations, the pressure fluctuations on the base wall feature dominant frequencies at SrD ≈ 0.05 and SrD ≈ 0.2-0.27, but are of small amplitudes (prms/p∞ = 0.02-0.025) compared to the main body boundary layer. For the nozzle dummy configuration, when moving downstream along the nozzle extension, the wall pressure is increasingly influenced by the reattaching shear layer and the periodic low-frequency behavior becomes less pronounced. Directly behind the reattachment point, the wall pressure reaches maximum mean and root-mean-square (rms) values of about p/p∞ = 1 and p'rms/p∞ = 0.1 and features a broadband specrms trum without distinct frequencies determined by the

  11. Hard Metal Disease

    PubMed Central

    Bech, A. O.; Kipling, M. D.; Heather, J. C.

    1962-01-01

    In Great Britain there have been no published reports of respiratory disease occurring amongst workers in the hard metal (tungsten carbide) industry. In this paper the clinical and radiological findings in six cases and the pathological findings in one are described. In two cases physiological studies indicated mild alveolar diffusion defects. Histological examination in a fatal case revealed diffuse pulmonary interstitial fibrosis with marked peribronchial and perivascular fibrosis and bronchial epithelial hyperplasia and metaplasia. Radiological surveys revealed the sporadic occurrence and low incidence of the disease. The alterations in respiratory mechanics which occurred in two workers following a day's exposure to dust are described. Airborne dust concentrations are given. The industrial process is outlined and the literature is reviewed. The toxicity of the metals is discussed, and our findings are compared with those reported from Europe and the United States. We are of the opinion that the changes which we would describe as hard metal disease are caused by the inhalation of dust at work and that the component responsible may be cobalt. Images PMID:13970036

  12. Simulation of the acoustic environment of a launcher and of the noise-induced vibrations on its structures

    NASA Astrophysics Data System (ADS)

    Bourgine, A.

    1983-03-01

    During the launching and transonic flight of a launcher, high level and wide-band frequency vibrations are transmitted to the payload and equipments. Preliminary simulation tests are planned to reproduce these dangerous phenomena; however, classical test facilities (reverberant acoustic chambers) generally do not provide simultaneously the true space and time distribution of the flight pressure fluctuations. A method is described for forcing the vibratory response of the launcher wall, for instance at the shroud which shelters the satellite. (Statistical characteristics of this response are known by a previous analytical prediction). Forced vibrations are produced by using a few number of electrodynamic shakers acting on the wall; the N random forces are simultaneously synthesized on a digital computer. The proper simulation is realized when measured responses at N points exhibit spectral distributions and overall RMS levels very close to the predicted flight values. Then, the noise level inside the shroud and the vibrations transmitted to the payload are also very close to the flight conditions. Some examples of applications to realistic structures, as the shroud of the Ariane vehicle, are presented.

  13. Technology for the European Next Generation Launcher - Integrated On-Ground and In-Flight Development Approach

    NASA Astrophysics Data System (ADS)

    Boggiato, D.; da Costa, R.; Tumino, T. Franck. G.

    ESA's Future Launcher Preparatory Programme (FLPP) includes system activities and technology developments, especially on materials and structures and on propulsion. The overall approach is system-driven, i.e. FLPP aims at defining reference launcher concepts from which technology development needs are derived, and a corresponding demonstration logic and scenario - including in-flight experimentation vehicles. This paper addresses the activities in the frame of the technology identification and verification process, which was concluded with the choice of a preferred demonstrator concept. The activities consisted of: - the identification of the critical technologies and of their present and target readiness levels - the establishment of their associated verification needs - the establishment of a verification approach for each need (what to be tested and how, whether on-ground or in-flight) - the identification of possible in-flight demonstrator candidates for re- entry and re-use technologies - the trade-offs among demonstrator candidates based on their experimentation output potential, and optimization of the synergies with on-ground testing - the selection of preferred in-flight demonstrator concepts. The paper shows the above process, together with details and intermediate results of the work leading to the final choice. Additionally it gives a summary and an outlook into the next expected steps.

  14. Study on the eddy current damping of the spin dynamics of space debris from the Ariane launcher upper stages

    NASA Astrophysics Data System (ADS)

    Praly, N.; Hillion, M.; Bonnal, C.; Laurent-Varin, J.; Petit, N.

    2012-07-01

    This paper addresses the topic of damping of the spin dynamics of a spatial debris orbiting around the Earth. Such debris, which can consist of parts of heavy launchers such as the Ariane rocket under consideration in this article, are impacted by torques generated by eddy currents as their conducting non-ferromagnetic body orbits through the Earth magnetosphere. Several previous works have focused on describing this induction phenomenon and have proposed analysis of empirical observations of this particular and important effect which has attracted much attention since the number of spatial debris has emerged as a problem for the future of space programs, especially in low orbits. In this paper, we present a relatively comprehensive modeling of the induction phenomenon, by means of Maxwell's equations inside the conducting and non-ferromagnetic body. Through the generalized Ohm's law, we show how one can obtain a partial differential equation with Neumann's boundary conditions problem that, once solved, e.g. through a finite elements method, yields the values of induced currents and braking torques. The case of a depleted upper stage of a heavy launcher, having a cylindrical shape and thin walls is particularly studied. We show a methodology to estimate the decay-rate of the spinning velocity, which is proven to satisfy a first-order asymptotically stable linear dynamics. Special cases consisting of typical orbit of space debris are treated.

  15. Janka hardness using nonstandard specimens

    Treesearch

    David W. Green; Marshall Begel; William Nelson

    2006-01-01

    Janka hardness determined on 1.5- by 3.5-in. specimens (2×4s) was found to be equivalent to that determined using the 2- by 2-in. specimen specified in ASTM D 143. Data are presented on the relationship between Janka hardness and the strength of clear wood. Analysis of historical data determined using standard specimens indicated no difference between side hardness...

  16. Overview: Hard Rock Penetration

    SciTech Connect

    Dunn, J.C.

    1992-08-01

    The Hard Rock Penetration program is developing technology to reduce the costs of drilling and completing geothermal wells. Current projects include: lost circulation control, rock penetration mechanics, instrumentation, and industry/DOE cost shared projects of the Geothermal Drilling organization. Last year, a number of accomplishments were achieved in each of these areas. A new flow meter being developed to accurately measure drilling fluid outflow was tested extensively during Long Valley drilling. Results show that this meter is rugged, reliable, and can provide useful measurements of small differences in fluid inflow and outflow rates. By providing early indications of fluid gain or loss, improved control of blow-out and lost circulation problems during geothermal drilling can be expected. In the area of downhole tools for lost circulation control, the concept of a downhole injector for injecting a two-component, fast-setting cementitious mud was developed. DOE filed a patent application for this concept during FY 91. The design criteria for a high-temperature potassium, uranium, thorium logging tool featuring a downhole data storage computer were established, and a request for proposals was submitted to tool development companies. The fundamental theory of acoustic telemetry in drill strings was significantly advanced through field experimentation and analysis. A new understanding of energy loss mechanisms was developed.

  17. Overview - Hard Rock Penetration

    SciTech Connect

    Dunn, James C.

    1992-03-24

    The Hard Rock Penetration program is developing technology to reduce the costs of drilling and completing geothermal wells. Current projects include: lost circulation control, rock penetration mechanics, instrumentation, and industry/DOE cost shared projects of the Geothermal Drilling Organization. Last year, a number of accomplishments were achieved in each of these areas. A new flow meter being developed to accurately measure drilling fluid outflow was tested extensively during Long Valley drilling. Results show that this meter is rugged, reliable, and can provide useful measurements of small differences in fluid inflow and outflow rates. By providing early indications of fluid gain or loss, improved control of blow-out and lost circulation problems during geothermal drilling can be expected. In the area of downhole tools for lost circulation control, the concept of a downhole injector for injecting a two-component, fast-setting cementitious mud was developed. DOE filed a patent application for this concept during FY 91. The design criteria for a high-temperature potassium, uranium, thorium logging tool featuring a downhole data storage computer were established, and a request for proposals was submitted to tool development companies. The fundamental theory of acoustic telemetry in drill strings was significantly advanced through field experimentation and analysis. A new understanding of energy loss mechanisms was developed.

  18. Overview: Hard Rock Penetration

    SciTech Connect

    Dunn, J.C.

    1992-01-01

    The Hard Rock Penetration program is developing technology to reduce the costs of drilling and completing geothermal wells. Current projects include: lost circulation control, rock penetration mechanics, instrumentation, and industry/DOE cost shared projects of the Geothermal Drilling organization. Last year, a number of accomplishments were achieved in each of these areas. A new flow meter being developed to accurately measure drilling fluid outflow was tested extensively during Long Valley drilling. Results show that this meter is rugged, reliable, and can provide useful measurements of small differences in fluid inflow and outflow rates. By providing early indications of fluid gain or loss, improved control of blow-out and lost circulation problems during geothermal drilling can be expected. In the area of downhole tools for lost circulation control, the concept of a downhole injector for injecting a two-component, fast-setting cementitious mud was developed. DOE filed a patent application for this concept during FY 91. The design criteria for a high-temperature potassium, uranium, thorium logging tool featuring a downhole data storage computer were established, and a request for proposals was submitted to tool development companies. The fundamental theory of acoustic telemetry in drill strings was significantly advanced through field experimentation and analysis. A new understanding of energy loss mechanisms was developed.

  19. Measuring the Hardness of Minerals

    ERIC Educational Resources Information Center

    Bushby, Jessica

    2005-01-01

    The author discusses Moh's hardness scale, a comparative scale for minerals, whereby the softest mineral (talc) is placed at 1 and the hardest mineral (diamond) is placed at 10, with all other minerals ordered in between, according to their hardness. Development history of the scale is outlined, as well as a description of how the scale is used…

  20. RF Behavior and Launcher Design for a Fast Frequency Step-tunable 236 GHz Gyrotron for DEMO

    NASA Astrophysics Data System (ADS)

    Kalaria, P. C.; Avramidis, K. A.; Franck, J.; Gantenbein, G.; Illy, S.; Jin, J.; Pagonakis, I. Gr.; Thumm, M.; Jelonnek, J.

    2017-03-01

    As part of the EUROfusion project, the conceptual design of a 1 MW 236 GHz hollow-cavity gyrotron is ongoing at IHM, KIT for a DEMOnstration Power Plant (DEMO), along with a 2 MW coaxial-cavity design concept. Fast frequency-tunable gyrotrons (tuning within a few seconds) are recommended for plasma stabilization using a non-steerable antenna. In this work, the mode-selection approach for such a frequency-tunable gyrotron is presented and suitable operating modes for fast frequency tunability are suggested. Magnetic field tuning has been studied as an effective technique to tune the gyrotron operating frequency. The step-tunability of the 236 GHz gyrotron within the frequency range of ±10 GHz in steps of 2-3 GHz is demonstrated in numerical simulations. A hybrid-type Quasi-Optical Launcher (QOL) has been designed for a step-frequency tunable gyrotron with sufficiently high Fundamental Gaussian Mode Content (FGMC).

  1. Characteristics of surface-wave and volume-wave plasmas produced with internally mounted large-area planar microwave launcher

    SciTech Connect

    Nagatsu, Masaaki; Naito, Katsutoshi; Ogino, Akihisa; Ninomiya, Keigo; Nanko, Shohei

    2005-10-17

    We studied discharge characteristics of microwave plasmas excited with a large-area planar microwave launcher installed internally in a 600-mm-diam cylindrical vacuum chamber. With the microwave power less than roughly 400 W, we demonstrated the large volumetric volume-wave plasma (VWP) spread in the entire chamber at a pressure of 14-27 Pa in He. Above 400 W, the plasma discharge made a sudden transition to higher-density, uniform surface-wave plasma (SWP) having a spatial uniformity of {+-}3.5% over 300 mm in diameter. Electron energy probability functions in the downstream region were studied using Langmuir probe measurements with Druyvesteyn method in both the SWP and VWP discharges.

  2. Palaeoecology and evolution of marine hard substrate communities

    NASA Astrophysics Data System (ADS)

    Taylor, P. D.; Wilson, M. A.

    2003-07-01

    Marine organisms have occupied hard substrates since the Archaean. Shells, rocks, wood and sedimentary hardgrounds offer relatively stable habitats compared to unconsolidated sediments, but the plants and animals which inhabit them must develop means to gain and defend this premium attachment space. Hard substrate communities are formed by organisms with a variety of strategies for adhering to and/or excavating the substrates they inhabit. While mobile grazers, organically attached and even soft-bodied organisms may leave evidence of their former presence in ancient hard substrate communities, a superior fossil record is left by sessile encrusters with mineralised skeletons and by borers which leave trace fossils. Furthermore, encrusters and borers are preserved in situ, retaining their spatial relationships to one another and to the substrate. Spatial competition, ecological succession, oriented growth, and differential utilisation of exposed vs. hidden substrate surfaces can all be observed or inferred. Hard substrate communities are thus excellent systems with which to study community evolution over hundreds of millions of years. Here we review the research on modern and ancient hard substrate communities, and point to some changes that have affected them over geological time scales. Such changes include a general increase in bioerosion of hard substrates, particularly carbonate surfaces, through the Phanerozoic. This is, at least in part, analogous to the infaunalisation trends seen in soft substrate communities. Encrusting forms show an increase in skeletalisation from the Palaeozoic into the Mesozoic and Cenozoic, which may be a response to increasing levels of predation. Hard substrate communities, considering borers and encrusters together, show a rough increase in tiering through the Phanerozoic which again parallels trends seen in soft substrate communities. This extensive review of the literature on living and fossil hard substrate organisms shows that

  3. Reviews Book: Enjoyable Physics Equipment: SEP Colorimeter Box Book: Pursuing Power and Light Equipment: SEP Bottle Rocket Launcher Equipment: Sciencescope GLE Datalogger Equipment: EDU Logger Book: Physics of Sailing Book: The Lightness of Being Software: Logotron Insight iLog Studio iPhone Apps Lecture: 2010 IOP Schools and Colleges Lecture Web Watch

    NASA Astrophysics Data System (ADS)

    2010-09-01

    WE RECOMMEND Enjoyable Physics Mechanics book makes learning more fun SEP Colorimeter Box A useful and inexpensive colorimeter for the classroom Pursuing Power and Light Account of the development of science in the 19th centuary SEP Bottle Rocket Launcher An excellent resource for teaching about projectiles GLE Datalogger GPS software is combined with a datalogger EDU Logger Remote datalogger has greater sensing abilities Logotron Insight iLog Studio Software enables datlogging, data analysis and modelling iPhone Apps Mobile phone games aid study of gravity WORTH A LOOK Physics of Sailing Book journeys through the importance of physics in sailing The Lightness of Being Study of what the world is made from LECTURE The 2010 IOP Schools and Colleges Lecture presents the physics of fusion WEB WATCH Planet Scicast pushes boundaries of pupil creativity

  4. Beta Backscatter Measures the Hardness of Rubber

    NASA Technical Reports Server (NTRS)

    Morrissey, E. T.; Roje, F. N.

    1986-01-01

    Nondestructive testing method determines hardness, on Shore scale, of room-temperature-vulcanizing silicone rubber. Measures backscattered beta particles; backscattered radiation count directly proportional to Shore hardness. Test set calibrated with specimen, Shore hardness known from mechanical durometer test. Specimen of unknown hardness tested, and radiation count recorded. Count compared with known sample to find Shore hardness of unknown.

  5. Thin coatings and films hardness evaluation

    NASA Astrophysics Data System (ADS)

    Matyunin, V. M.; Marchenkov, A. Yu; Demidov, A. N.; Karimbekov, M. A.

    2016-10-01

    The existing thin coatings and films hardness evaluation methods based on indentation with pyramidal indenter on various scale levels are expounded. The impact of scale factor on hardness values is performed. The experimental verification of several existing hardness evaluation methods regarding the substrate hardness value and the “coating - substrate” composite hardness value is made.

  6. Beta Backscatter Measures the Hardness of Rubber

    NASA Technical Reports Server (NTRS)

    Morrissey, E. T.; Roje, F. N.

    1986-01-01

    Nondestructive testing method determines hardness, on Shore scale, of room-temperature-vulcanizing silicone rubber. Measures backscattered beta particles; backscattered radiation count directly proportional to Shore hardness. Test set calibrated with specimen, Shore hardness known from mechanical durometer test. Specimen of unknown hardness tested, and radiation count recorded. Count compared with known sample to find Shore hardness of unknown.

  7. Nanoindentation hardness of mineralized tissues.

    PubMed

    Oyen, Michelle L

    2006-01-01

    A series elastic and plastic deformation model [Sakai, M., 1999. The Meyer hardness: a measure for plasticity? Journal of Materials Research 14(9), 3630-3639] is used to deconvolute the resistance to plastic deformation from the plane strain modulus and contact hardness parameters obtained in a nanoindentation test. Different functional dependencies of contact hardness on the plane strain modulus are examined. Plastic deformation resistance values are computed from the modulus and contact hardness for engineering materials and mineralized tissues. Elastic modulus and plastic deformation resistance parameters are used to calculate elastic and plastic deformation components, and to examine the partitioning of indentation deformation between elastic and plastic. Both the numerical values of plastic deformation resistance and the direct computation of deformation partitioning reveal the intermediate mechanical responses of mineralized composites when compared with homogeneous engineering materials.

  8. Reducing False Alarms in Ion Mobility Spectrometry Detectors Determination of Accurate and Precise Ion Mobility Spectrometry Constants

    DTIC Science & Technology

    2014-01-01

    Hard-Sphere and Ab Initio Potentials 22nd International Conference on Ion Mobility Spectrometry; Asheville , North Carolina; July 27- August 1, 2014...Spectrometer: Validation of Instrumental Parameters and Initial Results 22nd International Conference on Ion Mobility Spectrometry; Asheville , North

  9. Mobile healthcare.

    PubMed

    Morgan, Stephen A; Agee, Nancy Howell

    2012-01-01

    Mobile technology's presence in healthcare has exploded over the past five years. The increased use of mobile devices by all segments of the US population has driven healthcare systems, providers, and payers to accept this new form of communication and to develop strategies to implement and leverage the use of mobile healthcare (mHealth) within their organizations and practices. As healthcare systems move toward a more value-driven model of care, patient centeredness and engagement are the keys to success. Mobile healthcare will provide the medium to allow patients to participate more in their care. Financially, mHealth brings to providers the ability to improve efficiency and deliver savings to both them and the healthcare consumer. However, mHealth is not without challenges. Healthcare IT departments have been reluctant to embrace this shift in technology without fully addressing security and privacy concerns. Providers have been hesitant to adopt mHealth as a form of communication with patients because it breaks with traditional models. Our healthcare system has just started the journey toward the development of mHealth. We offer an overview of the mobile healthcare environment and our approach to solving the challenges it brings to healthcare organizations.

  10. Solid colloids with surface-mobile linkers.

    PubMed

    van der Meulen, Stef A J; Helms, Gesa; Dogterom, Marileen

    2015-06-17

    In this report we review the possibilities of using colloids with surface mobile linkers for the study of colloidal self-assembly processes. A promising route to create systems with mobile linkers is the use of lipid (bi-)layers. These lipid layers can be either used in the form of vesicles or as coatings for hard colloids and emulsion droplets. Inside the lipid bilayers molecules can be inserted via membrane anchors. Due to the fluidity of the lipid bilayer, the anchored molecules remain mobile. The use of different lipid mixtures even allows creating Janus-like particles that exhibit directional bonding if linkers are used which have a preference for a certain lipid phase. In nature mobile linkers can be found e.g. as receptors in cells. Therefore, towards the end of the review, we also briefly address the possibility of using colloids with surface mobile linkers as model systems to mimic cell-cell interactions and cell adhesion processes.

  11. Solid colloids with surface-mobile linkers

    NASA Astrophysics Data System (ADS)

    van der Meulen, Stef A. J.; Helms, Gesa; Dogterom, Marileen

    2015-06-01

    In this report we review the possibilities of using colloids with surface mobile linkers for the study of colloidal self-assembly processes. A promising route to create systems with mobile linkers is the use of lipid (bi-)layers. These lipid layers can be either used in the form of vesicles or as coatings for hard colloids and emulsion droplets. Inside the lipid bilayers molecules can be inserted via membrane anchors. Due to the fluidity of the lipid bilayer, the anchored molecules remain mobile. The use of different lipid mixtures even allows creating Janus-like particles that exhibit directional bonding if linkers are used which have a preference for a certain lipid phase. In nature mobile linkers can be found e.g. as receptors in cells. Therefore, towards the end of the review, we also briefly address the possibility of using colloids with surface mobile linkers as model systems to mimic cell-cell interactions and cell adhesion processes.

  12. Laser Safety Evaluation of the Oscmar M203PI Grenade Launcher Simulator (GLS) and the Associated Umpire Control Gun

    SciTech Connect

    AUGUSTONI, ARNOLD L.

    2002-06-01

    A laser safety evaluation and pertinent output measurements were performed (during March and April 2002) on the M203PI Grenade Launcher Simulator (GLS) and its associated Umpire Control Gun manufactured by Oscmar International Limited, Auckland, New Zealand. The results were the Oscmar Umpire Gun is laser hazard Class 1 and can be used without restrictions. The radiant energy output of the Oscmar M203PI GLS, under ''Small Source'' criteria at 10 centimeters, is laser hazard Class 3b and not usable, under SNL policy, in force-on-force exercises. However, due to a relatively large exit diameter and an intentionally large beam divergence, to simulate a large area blast, the output beam geometry met the criteria for ''Extended Source'' viewing [ANSI Std. 2136.1-2000 (S.l)]. Under this ''Extended Source'' criteria the output of the M203PI GLS unit was, in fact, laser hazard Class 1 (eye safe), for 3 of the 4 possible modes of laser operation. The 4'h mode, ''Auto Fire'', which simulates a continuous grenade firing every second and is not used at SNL, was laser hazard Class 3a (under the ''Extended Source'' viewing criteria). The M203PI GLS does present a laser hazard Class 3a to aided viewing with binoculars inside 3 meters from the unit. Farther than 3 meters it is ''eye safe''. The M203PI GLS can be considered a Class 1 laser hazard and can be used under SNL policy with the following restrictions: (1) The M203PI GLS unit shall only be programmed for: the ''Single Fire'' (which, includes ''Rapid Fire'') and the ''Auto Align'' (used in adjusting the alignment of the grenade launcher simulator system to the target) modes of operation. (2) The M203PI GLS shall never be directed against personnel, using binoculars, inside of 3 meters. DOE Order 5480.16A, Firearms Safety, (Chapter 1)(5)(a)(8)(d) and DOE-STD-1091-96, Firearms Safety (Chapter 4); already prevents ESS laser engagement of personnel (with or without binoculars), ''closer than 10 feet (3.05 meters)''. Both of

  13. Mechanical Analysis of an SM 2 Blk IV restrained firing within a concentric canister launcher test unit

    SciTech Connect

    Kassner, M C; Kennedy, T C; Puttapitukporn, T; Rosen, R S

    1999-03-01

    The Office of Naval Research (ONR) and PMS512 have undertaken a program to develop a new Vertical Launching System (VLS) for future generation ships, such as the DD-21 Destroyer. The Naval Sea Systems Command Combat Weapons Program (NAVSEA 05K) and Naval Surface Warfare Center Dahlgren Division (NSWCDD) are working jointly with industry and universities to develop one such launcher design, the Concentric Canister Launcher (CCL). The basic CCL design consists of a tube made of two concentric cylinders; one end is open, the other is sealed with a hemispherical end cap. During firing, the missile exhaust gas is turned 180 degrees by the hemispherical end cap and flows through the annular space between inner and outer cylinders. Depending on the missile utilized and the particular service environment of the CCL, maximum temperatures within the cylinder material have been calculated to exceed 2000 F. In an earlier study [1], the authors determined the high temperature mechanical properties of several candidate alloys being considered for fabrication of the CCL. This study [1] found that, of these candidate materials, titanium alloys exhibit higher yield stresses than that of 316L stainless steel at temperatures up to about 1000 F; above 1500 F, the yield stress of 316L stainless steel is comparable to those of the titanium alloys. The 316L stainless steel was found to strain harden (increase its flow stress with increasing strain) at temperatures up to about 1800 F. The ability of the 316L stainless steel to strain harden at high temperatures may provide an added margin of safety for engineering design of the CCL. The objective of the current study was to perform a computer simulation of the structural response of a CCL during a restrained firing, one in which a SM-2 Blk IV missile would fail to exit the canister. A finite element model of the inner cylinder, outer cylinder, end rings (mounting brackets), and lateral restraints in the uptake was constructed. An elastic

  14. Production of Volume Wave Plasma with Internally Mounted Cylindrical Planar Microwave Launcher and Two-Dimensional Field Analysis Using Finite Difference Time Domain Method

    NASA Astrophysics Data System (ADS)

    Ogino, Akihisa; Naito, Katsutoshi; Terashita, Fumie; Nanko, Shohei; Nagatsu, Masaaki

    2005-02-01

    In this paper, we presented experimental results on the production of volume wave plasma (VWP) using an internally mounted cylindrical planar microwave launcher, for application to novel plasma processings, such as inner wall coating, impurity-free etching or internal sterilization of medical instruments using VWP. It was demonstrated that the ellipsoidal VWP is produced in front of a microwave launcher in He or Ar gas atmosphere. Numerical analyses of microwave fields radiated from a planar launcher have been carried out using the two-dimensional finite difference time domain (FDTD) method to determine the mechanism of VWP production in middle of the chamber. It was shown that the calculation results showed fairly good agreements with the experimental results measured using a dipole antenna probe. The spatial distributions of plasma density and the temperature of VWP were also measured using a double probe. It was found that the electron density is comparable to or slightly less than cutoff density of 7.4 × 1010 cm-3 corresponding to the microwave frequency of fm=2.45 GHz, and that the electron temperature is approximately 6 eV at the plasma center.

  15. Optimizing mobilization strategies in difficult-to-mobilize patients: The role of plerixafor.

    PubMed

    Goker, Hakan; Etgul, Sezgin; Buyukasik, Yahya

    2015-08-01

    Peripheral blood stem cell collection is currently the most widely used source for hematopoietic autologous transplantation. Several factors such as advanced age, previous chemotherapy, disease and marrow infiltration at the time of mobilization influence the efficacy of CD34(+) progenitor cell mobilization. Despite the safety and efficiency of the standard mobilization protocols (G-CSF ± chemotherapy), there is still a significant amount of mobilization failure rate (10-40%), which necessitate novel agents for effective mobilization. Plerixafor, is a novel agent, has been recently approved for mobilization of hematopoietic stem cells (HSCs). The combination of Plerixafor with G-CSF provides the collection of large numbers of stem cells in fewer apheresis sessions and can salvage those who fail with standard mobilization regimens. The development and optimization of practical algorithms for the use Plerixafor is crucial to make hematopoietic stem cell mobilization more efficient in a cost-effective way. This review is aimed at summarizing how to identify poor mobilizers, and define rational use of Plerixafor for planning mobilization in hard-to-mobilize patients.

  16. Mobile microrobots for bioengineering applications.

    PubMed

    Ceylan, Hakan; Giltinan, Joshua; Kozielski, Kristen; Sitti, Metin

    2017-05-16

    Untethered micron-scale mobile robots can navigate and non-invasively perform specific tasks inside unprecedented and hard-to-reach inner human body sites and inside enclosed organ-on-a-chip microfluidic devices with live cells. They are aimed to operate robustly and safely in complex physiological environments where they will have a transforming impact in bioengineering and healthcare. Research along this line has already demonstrated significant progress, increasing attention, and high promise over the past several years. The first-generation microrobots, which could deliver therapeutics and other cargo to targeted specific body sites, have just been started to be tested inside small animals toward clinical use. Here, we review frontline advances in design, fabrication, and testing of untethered mobile microrobots for bioengineering applications. We convey the most impactful and recent strategies in actuation, mobility, sensing, and other functional capabilities of mobile microrobots, and discuss their potential advantages and drawbacks to operate inside complex, enclosed and physiologically relevant environments. We lastly draw an outlook to provide directions in the veins of more sophisticated designs and applications, considering biodegradability, immunogenicity, mobility, sensing, and possible medical interventions in complex microenvironments.

  17. Hard Work and Hard Data: Getting Our Message Out.

    ERIC Educational Resources Information Center

    Glau, Gregory R.

    Unless questions about student performance and student retention can be answered and unless educators are proactive in finding and publicizing such information, basic writing programs cannot determine if what they are doing is working. Hard data, especially from underrepresented groups, is needed to support these programs. At Arizona State…

  18. Hypervelocity Impact Testing of International Space Station Meteoroid/Orbital Debris Shielding Using an Inhibited Shaped Charge Launcher

    NASA Technical Reports Server (NTRS)

    Kerr, Justin H.; Grosch, Donald

    2001-01-01

    Engineers at the NASA Johnson Space Center have conducted hypervelocity impact (HVI) performance evaluations of spacecraft meteoroid and orbital debris (M/OD) shields at velocities in excess of 7 km/s. The inhibited shaped charge launcher (ISCL), developed by the Southwest Research Institute, launches hollow, circular, cylindrical jet tips to approximately 11 km/s. Since traditional M/OD shield ballistic limit performance is defined as the diameter of sphere required to just perforate or spall a spacecraft pressure wall, engineers must decide how to compare ISCL derived data with those of the spherical impactor data set. Knowing the mass of the ISCL impactor, an equivalent sphere diameter may be calculated. This approach is conservative since ISCL jet tips are more damaging than equal mass spheres. A total of 12 tests were recently conducted at the Southwest Research Institute (SWRI) on International Space Station M/OD shields. Results of these tests are presented and compared to existing ballistic limit equations. Modification of these equations is suggested based on the results.

  19. Magnetic levitation for hard superconductors

    SciTech Connect

    Kordyuk, A.A.

    1998-01-01

    An approach for calculating the interaction between a hard superconductor and a permanent magnet in the field-cooled case is proposed. The exact solutions were obtained for the point magnetic dipole over a flat ideally hard superconductor. We have shown that such an approach is adaptable to a wide practical range of melt-textured high-temperature superconductors{close_quote} systems with magnetic levitation. In this case, the energy losses can be calculated from the alternating magnetic field distribution on the superconducting sample surface. {copyright} {ital 1998 American Institute of Physics.}

  20. Future hard disk drive systems

    NASA Astrophysics Data System (ADS)

    Wood, Roger

    2009-03-01

    This paper briefly reviews the evolution of today's hard disk drive with the additional intention of orienting the reader to the overall mechanical and electrical architecture. The modern hard disk drive is a miracle of storage capacity and function together with remarkable economy of design. This paper presents a personal view of future customer requirements and the anticipated design evolution of the components. There are critical decisions and great challenges ahead for the key technologies of heads, media, head-disk interface, mechanics, and electronics.