KSC-06pd0578

NASA Image and Video Library

2006-04-06

KENNEDY SPACE CENTER, FLA. - In Orbiter Processing Facility bay 2 at NASA's Kennedy Space Center, the reinforced carbon-carbon nose cap has been installed on Endeavour. The nose cap has been insulated with thermal protection system blankets made of a woven ceramic fabric. The special blankets help insulate the vehicle's nose cap and protect it from the extreme temperatures it will face during a mission. Photo credit: NASA/Jim Grossmann

KSC-06pd0580

NASA Image and Video Library

2006-04-06

KENNEDY SPACE CENTER, FLA. - The reinforced carbon-carbon nose cap has been installed on Endeavour in Orbiter Processing Facility bay 2 at NASA's Kennedy Space Center. The nose cap has been insulated with thermal protection system blankets made of a woven ceramic fabric. The special blankets help insulate the vehicle's nose cap and protect it from the extreme temperatures it will face during a mission. Photo credit: NASA/Jim Grossmann

A methodology for accident analysis of fusion breeder blankets and its application to helium-cooled lead–lithium blanket

DOE PAGES

Panayotov, Dobromir; Poitevin, Yves; Grief, Andrew; ...

2016-09-23

'Fusion for Energy' (F4E) is designing, developing, and implementing the European Helium-Cooled Lead-Lithium (HCLL) and Helium-Cooled Pebble-Bed (HCPB) Test Blanket Systems (TBSs) for ITER (Nuclear Facility INB-174). Safety demonstration is an essential element for the integration of these TBSs into ITER and accident analysis is one of its critical components. A systematic approach to accident analysis has been developed under the F4E contract on TBS safety analyses. F4E technical requirements, together with Amec Foster Wheeler and INL efforts, have resulted in a comprehensive methodology for fusion breeding blanket accident analysis that addresses the specificity of the breeding blanket designs, materials,more » and phenomena while remaining consistent with the approach already applied to ITER accident analyses. Furthermore, the methodology phases are illustrated in the paper by its application to the EU HCLL TBS using both MELCOR and RELAP5 codes.« less

KSC-06pd0579

NASA Image and Video Library

2006-04-06

KENNEDY SPACE CENTER, FLA. - In Orbiter Processing Facility bay 2 at NASA's Kennedy Space Center, a worker checks the reinforced carbon-carbon nose cap after installation on Endeavour. The nose cap has been insulated with thermal protection system blankets made of a woven ceramic fabric. The special blankets help insulate the vehicle's nose cap and protect it from the extreme temperatures it will face during a mission. Photo credit: NASA/Jim Grossmann

KSC-05pd2513

NASA Image and Video Library

2005-11-19

KENNEDY SPACE CENTER, FLA. - Inside the RLV Hangar at NASA Kennedy Space Center, employees prepare a blanket sewing machine to be transferred back to the Thermal Protection System (TPS) facility. The upper floor of the facility, where soft material was processed, was damaged during the 2004 hurricanes. While the TPS facility was being repaired, normal work activity was done in the hangar.

KSC-06pd0575

NASA Image and Video Library

2006-04-05

KENNEDY SPACE CENTER, FLA. - In Orbiter Processing Facility bay 2 at NASA's Kennedy Space Center, workers are nearby as a crane lifts the reinforced carbon-carbon nose cap to be installed onto Endeavour. The nose cap is insulated with thermal protection system blankets made of a woven ceramic fabric. The special blankets help insulate the vehicle's nose cap and protect it from the extreme temperatures it will face during a mission. Photo credit: NASA/Jim Grossmann

KSC-06pd0577

NASA Image and Video Library

2006-04-05

KENNEDY SPACE CENTER, FLA. - In Orbiter Processing Facility bay 2 at NASA's Kennedy Space Center, a worker examines the underside of the reinforced carbon-carbon nose cap that will be installed on Endeavour. The nose cap is insulated with thermal protection system blankets made of a woven ceramic fabric. The special blankets help insulate the vehicle's nose cap and protect it from the extreme temperatures it will face during a mission. Photo credit: NASA/George Shelton

KSC-06pd0574

NASA Image and Video Library

2006-04-05

KENNEDY SPACE CENTER, FLA. - In Orbiter Processing Facility bay 2 at NASA's Kennedy Space Center, workers are preparing to move and install the reinforced carbon-carbon nose cap (on the stand) onto Endeavour. The nose cap is insulated with thermal protection system blankets made of a woven ceramic fabric. The special blankets help insulate the vehicle's nose cap and protect it from the extreme temperatures it will face during a mission. Photo credit: NASA/Jim Grossmann

KSC-06pd0257

NASA Image and Video Library

2006-02-09

KENNEDY SPACE CENTER, FLA. - The thermal protection system blanket insulation (foreground) has been hand-sewn onto a frame before being installed inside Endeavour's Reinforced Carbon-Carbon nose cap, seen in the background, in the NASA Kennedy Space Center Orbiter Processing Facility bay 2. Made of a woven ceramic fabric, the special blankets are used to help insulate the vehicle's nose cap and protect it from the extreme temperatures it will face during a mission. Photo credit: NASA/Jack Pfaller.

Comparison of measured and calculated composition of irradiated EBR-II blanket assemblies.

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

Grimm, K. N.

1998-07-13

In anticipation of processing irradiated EBR-II depleted uranium blanket subassemblies in the Fuel Conditioning Facility (FCF) at ANL-West, it has been possible to obtain a limited set of destructive chemical analyses of samples from a single EBR-II blanket subassembly. Comparison of calculated values with these measurements is being used to validate a depletion methodology based on a limited number of generic models of EBR-II to simulate the irradiation history of these subassemblies. Initial comparisons indicate these methods are adequate to meet the operations and material control and accountancy (MC and A) requirements for the FCF, but also indicate several shortcomingsmore » which may be corrected or improved.« less

18 CFR 157.212 - Synthetic and liquefied natural gas facilities.

Code of Federal Regulations, 2010 CFR

2010-04-01

... natural gas facilities. 157.212 Section 157.212 Conservation of Power and Water Resources FEDERAL ENERGY REGULATORY COMMISSION, DEPARTMENT OF ENERGY REGULATIONS UNDER NATURAL GAS ACT APPLICATIONS FOR CERTIFICATES... 7 OF THE NATURAL GAS ACT Interstate Pipeline Blanket Certificates and Authorization Under Section 7...

18 CFR 157.212 - Synthetic and liquefied natural gas facilities.

Code of Federal Regulations, 2011 CFR

2011-04-01

... natural gas facilities. 157.212 Section 157.212 Conservation of Power and Water Resources FEDERAL ENERGY REGULATORY COMMISSION, DEPARTMENT OF ENERGY REGULATIONS UNDER NATURAL GAS ACT APPLICATIONS FOR CERTIFICATES... 7 OF THE NATURAL GAS ACT Interstate Pipeline Blanket Certificates and Authorization Under Section 7...

Progress on DCLL Blanket Concept

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

Wong, Clement; Abdou, M.; Katoh, Yutai

2013-09-01

Under the US Fusion Nuclear Science and Technology Development program, we have selected the Dual Coolant Lead Lithium concept (DCLL) as a reference blanket, which has the potential to be a high performance DEMO blanket design with a projected thermal efficiency of >40%. Reduced activation ferritic/martensitic (RAF/M) steel is used as the structural material. The self-cooled breeder PbLi is circulated for power conversion and for tritium breeding. A SiC-based flow channel insert (FCI) is used as a means for magnetohydrodynamic pressure drop reduction from the circulating liquid PbLi and as a thermal insulator to separate the high-temperature PbLi (~700°C) frommore » the helium-cooled RAF/M steel structure. We are making progress on related R&D needs to address critical Fusion Nuclear Science and Facility (FNSF) and DEMO blanket development issues. When performing the function as the Interface Coordinator for the DCLL blanket concept, we had been developing the mechanical design and performing neutronics, structural and thermal hydraulics analyses of the DCLL TBM module. We had estimated the necessary ancillary equipment that will be needed at the ITER site and a detailed safety impact report has been prepared. This provided additional understanding of the DCLL blanket concept in preparation for the FNSF and DEMO. This paper will be a summary report on the progress of the DCLL TBM design and R&Ds for the DCLL blanket concept.« less

KSC-05pd2515

NASA Image and Video Library

2005-11-19

KENNEDY SPACE CENTER, FLA. - One of the blanket sewing machines used on Thermal Protection System materials has been returned to the TPS facility. It was moved to the RLV Hangar at NASA Kennedy Space Center after the 2004 hurricanes damaged the upper floor, where soft material was processed, of the TPS facility. While the TPS facility was being repaired, normal work activity was done in the hangar.

KSC-06pd0576

NASA Image and Video Library

2006-04-05

KENNEDY SPACE CENTER, FLA. - In Orbiter Processing Facility bay 2 at NASA's Kennedy Space Center, workers maneuver the reinforced carbon-carbon nose cap as it is hoisted into the air. The nose cap will be installed on Endeavour. The nose cap is insulated with thermal protection system blankets made of a woven ceramic fabric. The special blankets help insulate the vehicle's nose cap and protect it from the extreme temperatures it will face during a mission. Photo credit: NASA/Jim Grossmann

76 FR 24473 - Transwestern Pipeline Company, LLC; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2011-05-02

... DEPARTMENT OF ENERGY Federal Energy Regulatory Commission [Docket No. CP11-191-000] Transwestern...,000 HP reciprocating gas engines, compressors, and ancillary facilities (Project Facilities) at its... to access the document. For assistance, contact FERC at [email protected] or call toll-free...

75 FR 45111 - Kinder Morgan Interstate Gas Transmission LLC; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-02

... certain mainline pipeline and ancillary facilities primarily to serve a new ethanol plant in Adams County... develop firm transportation to serve ethanol production facilities in the Midwest, KMIGT held an open... gas to serve its new ethanol plant located near Aurora, Nebraska. Accordingly, KMIGT proposes to...

77 FR 37036 - Williston Basin Interstate Pipeline Company; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-20

... operation of natural gas facilities in Sheridan County and Campbell County, Wyoming and modification of underground storage facilities at its Baker Storage Reservoir in Fallon County, Montana. The details of... firm storage deliverability from its Baker Storage Reservoir that it will use to make up for declining...

Thermochemical hydrogen production based on magnetic fusion

NASA Astrophysics Data System (ADS)

Krikorian, O. H.; Brown, L. C.

Preliminary results of a DoE study to define the configuration and production costs for a Tandem Mirror Reactor (TMR) heat source H2 fuel production plant are presented. The TMR uses the D-T reaction to produce thermal energy and dc electrical current, with an Li blanket employed to breed more H-3 for fuel. Various blanket designs are being considered, and the coupling of two of them, a heat pipe blanket to a Joule-boosted decomposer, and a two-temperature zone blanket to a fluidized bed decomposer, are discussed. The thermal energy would be used in an H2SO4 thermochemical cycler to produce the H2. The Joule-boosted decomposer, involving the use of electrically heated commercial SiC furnace elements to transfer process heat to the thermochemical H2 cycle, is found to yield H2 fuel at a cost of $12-14/GJ, which is the projected cost of fossil fuels in 30-40 yr, when the TMR H2 production facility would be operable.

Neutronics Evaluation of Lithium-Based Ternary Alloys in IFE Blankets

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

Jolodosky, A.; Fratoni, M.

Lithium is often the preferred choice as breeder and coolant in fusion blankets as it offers excellent heat transfer and corrosion properties, and most importantly, it has a very high tritium solubility and results in very low levels of tritium permeation throughout the facility infrastructure. However, lithium metal vigorously reacts with air and water and exacerbates plant safety concerns. For this reason, over the years numerous blanket concepts have been proposed with the scope of reducing concerns associated with lithium. The European helium cooled pebble bed breeding blanket (HCPB) physically confines lithium within ceramic pebbles. The pebbles reside within amore » low activation martensitic ferritic steel structure and are cooled by helium. The blanket is composed of the tritium breeding lithium ceramic pebbles and neutron multiplying beryllium pebbles. Other blanket designs utilize lead to lower chemical reactivity; LiPb alone can serve as a breeder, coolant, neutron multiplier, and tritium carrier. Blankets employing LiPb coolants alongside silicon carbide structural components can achieve high plant efficiency, low afterheat, and low operation pressures. This alloy can also be used alongside of helium such as in the dual-coolant lead-lithium concept (DCLL); helium is utilized to cool the first wall and structural components made up of low-activation ferritic steel, whereas lithium-lead (LiPb) acts as a self-cooled breeder in the inner channels of the blanket. The helium-cooled steel and lead-lithium alloy are separated by flow channel inserts (usually made out of silicon carbide) which thermally insulate the self-cooled breeder region from the helium cooled steel walls. This creates a LiPb breeder with a much higher exit temperature than the steel which increases the power cycle efficiency and also lowers the magnetohydrodynamic (MHD) pressure drop [6]. Molten salt blankets with a mixture of lithium, beryllium, and fluorides (FLiBe) offer good tritium breeding, low electrical conductivity and therefore low MHD pressure drop, low chemical reactivity, and extremely low tritium inventory; the addition of sodium (FLiNaBe) has been considered because it retains the properties of FliBe but also lowers the melting point. Although many of these blanket concepts are promising, challenges still remain. The limited amount of beryllium available poses a problem for ceramic breeders such as the HCPB. FLiBe and FLiNaBe are highly viscous and have a low thermal conductivity. Lithium lead possesses a poor thermal conductivity which can cause problems in both DCLL and LiPb blankets. Additionally, the tritium permeation from these two blankets into plant components can be a problem and must be reduced. Consequently, Lawrence Livermore National Laboratory (LLNL) is attempting to develop a lithium-based alloy—most likely a ternary alloy—which maintains the beneficial properties of lithium (e.g. high tritium breeding and solubility) while reducing overall flammability concerns for use in the blanket of an inertial fusion energy (IFE) power plant. The LLNL concept employs inertial confinement fusion (ICF) through the use of lasers aimed at an indirect-driven target composed of deuterium-tritium fuel. The fusion driver/target design implements the same physics currently experimented at the National Ignition Facility (NIF). The plant uses lithium in both the primary coolant and blanket; therefore, lithium-related hazards are of primary concern. Although reducing chemical reactivity is the primary motivation for the development of new lithium alloys, the successful candidates will have to guarantee acceptable performance in all their functions. The scope of this study is to evaluate the neutronics performance of a large number of lithium-based alloys in the blanket of the IFE engine and assess their properties upon activation. This manuscript is organized as follows: Section 12 presents the models and methodologies used for the analysis; Section 3 discusses the results; Section 4 summarizes findings and future work.« less

ARC: A compact, high-field, disassemblable fusion nuclear science facility and demonstration power plant

NASA Astrophysics Data System (ADS)

Sorbom, Brandon; Ball, Justin; Palmer, Timothy; Mangiarotti, Franco; Sierchio, Jennifer; Bonoli, Paul; Kasten, Cale; Sutherland, Derek; Barnard, Harold; Haakonsen, Christian; Goh, Jon; Sung, Choongki; Whyte, Dennis

2014-10-01

The Affordable, Robust, Compact (ARC) reactor conceptual design aims to reduce the size, cost, and complexity of a combined Fusion Nuclear Science Facility (FNSF) and demonstration fusion pilot power plant. ARC is a 270 MWe tokamak reactor with a major radius of 3.3 m, a minor radius of 1.1 m, and an on-axis magnetic field of 9.2 T. ARC has Rare Earth Barium Copper Oxide (REBCO) superconducting toroidal field coils with joints to allow disassembly, allowing for removal and replacement of the vacuum vessel as a single component. Inboard-launched current drive of 25 MW LHRF power and 13.6 MW ICRF power is used to provide a robust, steady state core plasma far from disruptive limits. ARC uses an all-liquid blanket, consisting of low pressure, slowly flowing Fluorine Lithium Beryllium (FLiBe) molten salt. The liquid blanket acts as a working fluid, coolant, and tritium breeder, and minimizes the solid material that can become activated. The large temperature range over which FLiBe is liquid permits blanket operation at 800-900 K with single phase fluid cooling and allows use of a high-efficiency Brayton cycle for electricity production in the secondary coolant loop.

M and D SIG progress report: Laboratory simulations of LDEF impact features

NASA Technical Reports Server (NTRS)

Horz, Friedrich; Bernhard, R. P.; See, Thomas H.; Atkinson, Dale R.; Allbrooks, Martha K.

1991-01-01

Reported here are impact simulations into pure Teflon and aluminum targets. These experiments will allow first order interpretations of impact features on the Long Duration Exposure Facility (LDEF), and they will serve as guides for dedicated experiments that employ the real LDEF blankets, both unexposed and exposed, for a refined understanding of the Long Duration Exposure Facility's collisional environment.

Task toward a Realization of Commercial Tokamak Fusion Plants in 2050 -The Role of ITER and the Succeeding Developments- 4.Technology and Material Research in Fusion Power Plant Development

NASA Astrophysics Data System (ADS)

Akiba, Masato; Matsui, Hideki; Takatsu, Hideyuki; Konishi, Satoshi

Technical issues regarding the fusion power plant that are required to be developed in the period of ITER construction and operation, both with ITER and with other facilities that complement ITER are described in this section. Three major fields are considered to be important in fusion technology. Section 4.1 summarizes blanket study, and ITER Test Blanket Module (TBM) development that focuses its effort on the first generation power blanket to be installed in DEMO. ITER will be equipped with 6 TBMs which are developed under each party's fusion program. In Japan, the solid breeder using water as a coolant is the primary candidate, and He-cooled pebble bed is the alternative. Other liquid options such as LiPb, Li or molten salt are developed by other parties' initiatives. The Test Blanket Working Group (TBWG) is coordinating these efforts. Japanese universities are investigating advanced concepts and fundamental crosscutting technologies. Section 4.2 introduces material development and particularly, the international irradiation facility, IFMIF. Reduced activation ferritic/martensitic steels are identified as promising candidates for the structural material of the first generation fusion blanket, while and vanadium alloy and SiC/SiC composite are pursued as advanced options. The IFMIF is currently planning the next phase of joint activity, EVEDA (Engineering Validation and Engineering Design Activity) that encompasses construction. Material studies together with the ITER TBM will provide essential technical information for development of the fusion power plant. Other technical issues to be addressed regarding the first generation fusion power plant are summarized in section 4.3. Development of components for ITER made remarkable progress for the major essential technology also necessary for future fusion plants, however many still need further improvements toward power plant. Such areas includes; the divertor, plasma heating/current drive, magnets, tritium, and remote handling. There remain many other technical issues for power plant which require integrated efforts.

Experimental impacts into Teflon targets and LDEF thermal blankets

NASA Astrophysics Data System (ADS)

Hoerz, F.; Cintala, M. J.; Zolensky, M. E.; Bernhard, R. P.; See, T. H.

1994-03-01

The Long Duration Exposure Facility (LDEF) exposed approximately 20 sq m of identical thermal protective blankets, predominantly on the Ultra-Heavy Cosmic Ray Experiment (UHCRE). Approximately 700 penetration holes greater than 300 micron in diameter were individually documented, while thousands of smaller penetrations and craters occurred in these blankets. As a result of their 5.7 year exposure and because they pointed into a variety of different directions relative to the orbital motion of the nonspinning LDEF platform, these blankets can reveal important dynamic aspects of the hypervelocity particle environment in near-earth orbit. The blankets were composed of an outer teflon layer (approximately 125 micron thick), followed by a vapor-deposited rear mirror of silver (less than 1000 A thick) that was backed with an organic binder and a thermal protective paint (approximately 50 to 75 micron thick), resulting in a cumulative thickness (T) of approximately 175 to 200 microns for the entire blanket. Many penetrations resulted in highly variable delaminations of the teflon/metal or metal/organic binder interfaces that manifest themselves as 'dark' halos or rings, because of subsequent oxidation of the exposed silver mirror. The variety of these dark albedo features is bewildering, ranging from totally absent, to broad halos, to sharp single or multiple rings. Over the past year experiments were conducted over a wide range of velocities (i.e., 1 to 7 km/s) to address velocity dependent aspects of cratering and penetrations of teflon targets. In addition, experiments were performed with real LDEF thermal blankets to duplicate the LDEF delaminations and to investigate a possible relationship of initial impact conditions on the wide variety of dark halo and ring features.

75 FR 24943 - Millennium Pipeline Company, LLC; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2010-05-06

... at a tie-in at Chambers Road near Horseheads, New York to an interconnection with the facilities of... to Gary A. Kruse, Vice President--General Counsel and Secretary, Millennium Pipeline Company, LLC...

Hypervelocity Impact Testing of Space Station Freedom Solar Cells

NASA Technical Reports Server (NTRS)

Christie, Robert J.; Best, Steve R.; Myhre, Craig A.

1994-01-01

Solar array coupons designed for the Space Station Freedom electrical power system were subjected to hypervelocity impacts using the HYPER facility in the Space Power Institute at Auburn University and the Meteoroid/Orbital Debris Simulation Facility in the Materials and Processes Laboratory at the NASA Marshall Space Flight Center. At Auburn, the solar cells and array blanket materials received several hundred impacts from particles in the micron to 100 micron range with velocities typically ranging from 4.5 to 10.5 km/s. This fluence of particles greatly exceeds what the actual components will experience in low earth orbit. These impacts damaged less than one percent of total area of the solar cells and most of the damage was limited to the cover glass. There was no measurable loss of electrical performance. Impacts on the array blanket materials produced even less damage and the blanket materials proved to be an effective shield for the back surface of the solar cells. Using the light gas gun at MSFC, one cell of a four cell coupon was impacted by a 1/4 inch spherical aluminum projectile with a velocity of about 7 km/s. The impact created a neat hole about 3/8 inch in diameter. The cell and coupon were still functional after impact.

KENNEDY SPACE CENTER, FLA. -- United Space Alliance (USA) Manager of the Thermal Protection System (TPS) Facility Martin Wilson (right) briefs NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (left) on the properties of a thermal blanket used in the Shuttle's TPS. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

NASA Image and Video Library

2003-12-19

KENNEDY SPACE CENTER, FLA. -- United Space Alliance (USA) Manager of the Thermal Protection System (TPS) Facility Martin Wilson (right) briefs NASA Deputy Associate Administrator for Space Station and Shuttle Programs Michael Kostelnik (left) on the properties of a thermal blanket used in the Shuttle's TPS. NASA and USA Space Shuttle program management are participating in a leadership workday. The day is intended to provide management with an in-depth, hands-on look at Shuttle processing activities at KSC.

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

Panayotov, Dobromir; Poitevin, Yves; Grief, Andrew

'Fusion for Energy' (F4E) is designing, developing, and implementing the European Helium-Cooled Lead-Lithium (HCLL) and Helium-Cooled Pebble-Bed (HCPB) Test Blanket Systems (TBSs) for ITER (Nuclear Facility INB-174). Safety demonstration is an essential element for the integration of these TBSs into ITER and accident analysis is one of its critical components. A systematic approach to accident analysis has been developed under the F4E contract on TBS safety analyses. F4E technical requirements, together with Amec Foster Wheeler and INL efforts, have resulted in a comprehensive methodology for fusion breeding blanket accident analysis that addresses the specificity of the breeding blanket designs, materials,more » and phenomena while remaining consistent with the approach already applied to ITER accident analyses. Furthermore, the methodology phases are illustrated in the paper by its application to the EU HCLL TBS using both MELCOR and RELAP5 codes.« less

76 FR 7189 - Trunkline Gas Company, LLC; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2011-02-09

... Ship Shoal T-27 Platform and appurtenant facilities located in Ship Shoal 274, Offshore Louisiana... as more fully set forth in the application, which is open to the public for inspection. The filing...

76 FR 14654 - Gulfstream Natural Gas System, L.L.C. Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-17

... design and construct, one 30-inch tie-in assembly connecting the outlet of the Gulf LNG Pipeline facilities to Gulfstream's 36-inch diameter Line No. 060, electronic gas measurement equipment, and...

Evaluation of Thermal Control Coatings for Flexible Ceramic Thermal Protection Systems

NASA Technical Reports Server (NTRS)

Kourtides, Demetrius; Carroll, Carol; Smith, Dane; Guzinski, Mike; Marschall, Jochen; Pallix, Joan; Ridge, Jerry; Tran, Duoc

1997-01-01

This report summarizes the evaluation and testing of high emissivity protective coatings applied to flexible insulations for the Reusable Launch Vehicle technology program. Ceramic coatings were evaluated for their thermal properties, durability, and potential for reuse. One of the major goals was to determine the mechanism by which these coated blanket surfaces become brittle and try to modify the coatings to reduce or eliminate embrittlement. Coatings were prepared from colloidal silica with a small percentage of either SiC or SiB6 as the emissivity agent. These coatings are referred to as gray C-9 and protective ceramic coating (PCC), respectively. The colloidal solutions were either brushed or sprayed onto advanced flexible reusable surface insulation blankets. The blankets were instrumented with thermocouples and exposed to reentry heating conditions in the Ames Aeroheating Arc Jet Facility. Post-test samples were then characterized through impact testing, emissivity measurements, chemical analysis, and observation of changes in surface morphology. The results show that both coatings performed well in arc jet tests with backface temperatures slightly lower for the PCC coating than with gray C-9. Impact testing showed that the least extensive surface destruction was experienced on blankets with lower areal density coatings.

An analysis of LDEF-exposed silvered FEP teflon thermal blanket material

NASA Technical Reports Server (NTRS)

Young, Philip R.; Slemp, Wayne S.

1991-01-01

The characterization of selected silvered fluorinated ethylene propylene (FEP) teflon thermal blanket material which received 5 years and 9 months of exposure to the LEO environment on the Long Duration Exposure Facility is reported. X-ray photoelectron spectroscopy, infrared, and thermal analyses did not detect a significant change at the molecular level as the result of this exposure. However, various microscopic analyses revealed a roughening of the coating surface due to atomic oxygen erosion which resulted in some materials changing from specular reflectors of visible radiation to diffuse reflectors. The potential effect of silicon-containing molecular contamination on these materials is addressed.

76 FR 80926 - Dominion Transmission, Inc; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2011-12-27

... approximately 735 feet of 8-inch diameter TL-369 Ext. 2 receiver pipeline facilities; and (3) construct two new... proposes to: (1) Replace approximately 14.98 miles of it's existing multi-diameter (12, 14, and 16-inch) TL...

75 FR 17708 - Kinder Morgan Louisiana Pipeline LLC; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2010-04-07

... authorization to construct and operate a new tap, including ball valve and riser and approximately 15 feet of 8..., riser, 15-feet of 8-inch diameter piping and such other appurtenant facilities as deemed necessary to...

TBM/MTM for HTS-FNSF: An innovative testing strategy to qualify/validate fusion technologies for U.S. DEMO

DOE PAGES

El-Guebaly, Laila; Rowcliffe, Arthur; Menard, Jonathan; ...

2016-08-11

The qualification and validation of nuclear technologies are daunting tasks for fusion demonstration (DEMO) and power plants. This is particularly true for advanced designs that involve harsh radiation environment with 14 MeV neutrons and high-temperature operating regimes. This paper outlines the unique qualification and validation processes developed in the U.S., offering the only access to the complete fusion environment, focusing on the most prominent U.S. blanket concept (the dual cooled PbLi (DCLL)) along with testing new generations of structural and functional materials in dedicated test modules. The venue for such activities is the proposed Fusion Nuclear Science Facility (FNSF), whichmore » is viewed as an essential element of the U.S. fusion roadmap. A staged blanket testing strategy has been developed to test and enhance the DCLL blanket performance during each phase of FNSF D-T operation. A materials testing module (MTM) is critically important to include in the FNSF as well to test a broad range of specimens of future, more advanced generations of materials in a relevant fusion environment. Here, the most important attributes for MTM are the relevant He/dpa ratio (10–15) and the much larger specimen volumes compared to the 10–500 mL range available in the International Fusion Materials Irradiation Facility (IFMIF) and European DEMO-Oriented Neutron Source (DONES).« less

KSC-98pc1164

NASA Image and Video Library

1998-09-28

The orbiter Atlantis is towed away from the Shuttle Landing Facility after returning home from California atop its Shuttle Carrier Aircraft. The orbiter spent 10 months in Palmdale undergoing extensive inspections and modifications in the orbiter processing facility there. The modifications included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. Atlantis will undergo preparations in the Orbiter Processing Facility at KSC for its planned flight in June 1999

Summary of solar cell data from the Long Duration Exposure Facility (LDEF)

NASA Technical Reports Server (NTRS)

Hill, David C.; Rose, M. Frank

1994-01-01

The Long Duration Exposure Facility (LDEF) was composed of many separate experiments, some of which contained solar cells. These solar cells were distributed at various positions on the LDEF and, therefore, were exposed to the space environment with an orientational dependence. This report will address the space environmental effects on solar cells and solar cell assemblies (SCA's), including electrical interconnects and associated insulation blankets where flown in conjunction with solar cells.

M and D SIG progress report: Laboratory simulations of LDEF impact features

NASA Technical Reports Server (NTRS)

Horz, Friedrich; Bernhard, R. P.; See, T. H.; Atkinson, D.; Allbrooks, M.

1992-01-01

Laboratory impact experiments are needed to understand the relationship between a measured penetration hole diameter and associated projectile dimension in the thermal blankets of experiment A0178, which occupied some 16 sq. m. These blankets are composed of 125 micron thick Teflon that has an Ag/enconel second mirror surface, backed by organic binder and Chemglaze paint for a total thickness of some 170 microns. While dedicated experiments are required to understand the penetration behavior of this compound target in detail, we report here on impact simulations sponsored by other projects into pure Teflon and aluminum targets. These experiments will allow first order interpretations of impact features on the Long Duration Exposure Facility (LDEF), and they will serve as guides for dedicated experiments that employ the real LDEF blankets, both exposed and unexposed, for a refined understanding of the LDEF's collisional environment. We employed a light gas gun to launch soda-lime glass spheres from 50 to 3200 microns in diameter that impacted targets of variable thickness. Penetration measurements are given.

KSC-98pc1166

NASA Image and Video Library

1998-09-28

The orbiter Atlantis, being towed from the Shuttle Landing Facility toward the Vehicle Assembly Building (VAB) , intersects the morning sun's rays. In the background, to the right of the VAB, are the Orbiter Processing Facility 1 and 2. Atlantis spent 10 months in Palmdale, CA, undergoing extensive inspections and modifications in the orbiter processing facility there. The modifications included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. Atlantis will undergo preparations at KSC in Orbiter Processing Facility 2 for its planned flight in June 1999

Maximal design basis accident of fusion neutron source DEMO-TIN

NASA Astrophysics Data System (ADS)

Kolbasov, B. N.

2015-12-01

When analyzing the safety of nuclear (including fusion) facilities, the maximal design basis accident at which the largest release of activity is expected must certainly be considered. Such an accident is usually the failure of cooling systems of the most thermally stressed components of a reactor (for a fusion facility, it is the divertor or the first wall). The analysis of safety of the ITER reactor and fusion power facilities (including hybrid fission-fusion facilities) shows that the initial event of such a design basis accident is a large-scale break of a pipe in the cooling system of divertor or the first wall outside the vacuum vessel of the facility. The greatest concern is caused by the possibility of hydrogen formation and the inrush of air into the vacuum chamber (VC) with the formation of a detonating mixture and a subsequent detonation explosion. To prevent such an explosion, the emergency forced termination of the fusion reaction, the mounting of shutoff valves in the cooling systems of the divertor and the first wall or blanket for reducing to a minimum the amount of water and air rushing into the VC, the injection of nitrogen or inert gas into the VC for decreasing the hydrogen and oxygen concentration, and other measures are recommended. Owing to a continuous feed-out of the molten-salt fuel mixture from the DEMO-TIN blanket with the removal period of 10 days, the radioactivity release at the accident will mainly be determined by tritium (up to 360 PBq). The activity of fission products in the facility will be up to 50 PBq.

18 CFR 157.210 - Mainline natural gas facilities.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 18 Conservation of Power and Water Resources 1 2010-04-01 2010-04-01 false Mainline natural gas... COMMISSION, DEPARTMENT OF ENERGY REGULATIONS UNDER NATURAL GAS ACT APPLICATIONS FOR CERTIFICATES OF PUBLIC... GAS ACT Interstate Pipeline Blanket Certificates and Authorization Under Section 7 of the Natural Gas...

Conceptual Design and Neutronics Analyses of a Fusion Reactor Blanket Simulation Facility

DTIC Science & Technology

1986-01-01

Laboratory (LLL) ORNL Oak Ridge National Laboratory PPPL Princeton Plasma Physics Laboratory RSIC Reactor Shielding Information Center (at ORNL) SS...Module (LBM) to be placed in the TFTR at PPPL . Jassby et al. describe the program, including design, manufacturing techniques. neutronics analyses, and

75 FR 33803 - Sabine Pipe Line LLC; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2010-06-15

... natural gas-driven compressor units totaling 2,464 horsepower. Sabine states that for the past several years, the Lake Charles Compressor Facilities have not been necessary to provide transportation services... comments, protests, and interventions via the Internet in lieu [[Page 33804

Low Earth orbital atomic oxygen micrometeoroid, and debris interactions with photovoltaic arrays

NASA Technical Reports Server (NTRS)

Banks, Bruce A.; Rutledge, Sharon K.; Degroh, Kim K.

1991-01-01

Polyimide Kapton solar array blankets can be protected from atomic oxygen in low earth orbit if SiO sub x thin film coatings are applied to their surfaces. The useful lifetime of a blanket protected in this manner strongly depends on the number and size of defects in the protective coatings. Atomic oxygen degradation is dominated by undercutting at defects in protective coatings caused by substrate roughness and processing rather than micrometeoroid or debris impacts. Recent findings from the Long Duration Exposure Facility (LDEF) and ground based studies show that interactions between atomic oxygen and silicones may cause grazing and contamination problems which may lead to solar array degradation.

Blanketing effect of expansion foam on liquefied natural gas (LNG) spillage pool.

PubMed

Zhang, Bin; Liu, Yi; Olewski, Tomasz; Vechot, Luc; Mannan, M Sam

2014-09-15

With increasing consumption of natural gas, the safety of liquefied natural gas (LNG) utilization has become an issue that requires a comprehensive study on the risk of LNG spillage in facilities with mitigation measures. The immediate hazard associated with an LNG spill is the vapor hazard, i.e., a flammable vapor cloud at the ground level, due to rapid vaporization and dense gas behavior. It was believed that high expansion foam mitigated LNG vapor hazard through warming effect (raising vapor buoyancy), but the boil-off effect increased vaporization rate due to the heat from water drainage of foam. This work reveals the existence of blocking effect (blocking convection and radiation to the pool) to reduce vaporization rate. The blanketing effect on source term (vaporization rate) is a combination of boil-off and blocking effect, which was quantitatively studied through seven tests conducted in a wind tunnel with liquid nitrogen. Since the blocking effect reduces more heat to the pool than the boil-off effect adds, the blanketing effect contributes to the net reduction of heat convection and radiation to the pool by 70%. Water drainage rate of high expansion foam is essential to determine the effectiveness of blanketing effect, since water provides the boil-off effect. Copyright © 2014 Elsevier B.V. All rights reserved.

18 CFR 157.215 - Underground storage testing and development.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 7 OF THE NATURAL GAS ACT Interstate Pipeline Blanket Certificates and Authorization Under Section 7..., construct and operate natural gas pipeline and compression facilities, including injection, withdrawal, and... the gas bubble. This map need not be filed if there is no material change from the map previously...

78 FR 65639 - Questar Pipeline Company; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-01

... DEPARTMENT OF ENERGY Federal Energy Regulatory Commission [Docket No. CP14-6-000] Questar Pipeline... appurtenant facilities located in Moffat County, Colorado. Specifically, Questar proposes to abandon one Solar Saturn 1200 compressor, a compressor building, two generators and a generator building, a liquids storage...

KSC-04pd1770

NASA Image and Video Library

2004-09-10

KENNEDY SPACE CENTER, FLA. - Members of a hurricane assessment team from Johnson Space Center and Marshall Space Flight Center tour the Thermal Protection System (TPS) Facility at KSC after Hurricane Frances hit the east coast of Central Florida and Kennedy Space Center. At left is Martin Wilson, manager of the TPS operations. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof. Equipment and materials that survived the storm have been relocated to the RLV hangar near the KSC Shuttle Landing Facility.

KSC-98pc1165

NASA Image and Video Library

1998-09-28

The orbiter Atlantis, being towed from the Shuttle Landing Facility, is reflected in waters from the Banana Creek next to the towway. The orbiter spent 10 months in Palmdale, CA, undergoing extensive inspections and modifications in the orbiter processing facility there. The modifications included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. Atlantis will undergo preparations in the Orbiter Processing Facility at KSC for its planned flight in June 1999

KSC-04pd1774

NASA Image and Video Library

2004-09-10

KENNEDY SPACE CENTER, FLA. - Members of a hurricane assessment team from Johnson Space Center and Marshall Space Flight Center observe the damage to the roof of the Thermal Protection System (TPS) Facility at KSC after Hurricane Frances hit the east coast of Central Florida and Kennedy Space Center. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof. Equipment and materials that survived the storm have been relocated to the RLV hangar near the KSC Shuttle Landing Facility.

Maximal design basis accident of fusion neutron source DEMO-TIN

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

Kolbasov, B. N., E-mail: Kolbasov-BN@nrcki.ru

2015-12-15

When analyzing the safety of nuclear (including fusion) facilities, the maximal design basis accident at which the largest release of activity is expected must certainly be considered. Such an accident is usually the failure of cooling systems of the most thermally stressed components of a reactor (for a fusion facility, it is the divertor or the first wall). The analysis of safety of the ITER reactor and fusion power facilities (including hybrid fission–fusion facilities) shows that the initial event of such a design basis accident is a large-scale break of a pipe in the cooling system of divertor or themore » first wall outside the vacuum vessel of the facility. The greatest concern is caused by the possibility of hydrogen formation and the inrush of air into the vacuum chamber (VC) with the formation of a detonating mixture and a subsequent detonation explosion. To prevent such an explosion, the emergency forced termination of the fusion reaction, the mounting of shutoff valves in the cooling systems of the divertor and the first wall or blanket for reducing to a minimum the amount of water and air rushing into the VC, the injection of nitrogen or inert gas into the VC for decreasing the hydrogen and oxygen concentration, and other measures are recommended. Owing to a continuous feed-out of the molten-salt fuel mixture from the DEMO-TIN blanket with the removal period of 10 days, the radioactivity release at the accident will mainly be determined by tritium (up to 360 PBq). The activity of fission products in the facility will be up to 50 PBq.« less

Space environmental effects on silvered Teflon thermal control surfaces

NASA Technical Reports Server (NTRS)

Hemminger, C. S.; Stuckey, W. K.; Uht, J. C.

1991-01-01

Cumulative space environment effects on Ag/fluorinated ethylene propylene (FEP) were a function of exposure orientation. Samples from nineteen silvered Teflon (Ag/FEP) thermal control surfaces recovered from the Long Duration Exposure Facility (LDEF) were analyzed to determine changes in this material as a function of position on the spacecraft. Although solar absorptance and infrared emittance of measured thermal blanket specimens are relatively unchanged from control specimen values, significant changes in surface morphology, composition and chemistry were observed. Researchers hypothesize that the FEP surfaces on LDEF were degraded by ultraviolet radiation exposure at all orientations, but that the damaged material had been removed by erosion from the blankets exposed to atomic oxygen flux and that contamination is masking the damage on trays flanking the trailing edge.

KSC-2012-1961

NASA Image and Video Library

2012-04-05

CAPE CANAVERAL, Fla. – Kennedy Space Center Director Bob Cabana, right, shows a space shuttle felt reusable surface insulation FRSI blanket to Florida’s Lt. Gov. Jennifer Carroll during a tour of Kennedy’s Orbiter Processing Facility-1. The blanket is part of the shuttle’s thermal protection system which covers the shuttle’s exterior and protects it from the heat of re-entry. The tour coincided with Carroll’s visit to Kennedy for a meeting with Cabana. Atlantis is being prepared for public display at the Kennedy Space Center Visitor Complex in 2013. The groundbreaking for Atlantis’ exhibit hall took place in January Atlantis is scheduled to be moved to the visitor complex in November. For more information, visit http://www.nasa.gov/shuttle. Photo credit: NASA/Jim Grossmann

76 FR 28972 - Eastern Shore Natural Gas Company; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2011-05-19

.... Eastern Shore will recover its project costs entirely from Chesapeake, with no subsidy from Eastern Shore's other firm service customers. The total estimate cost of the proposed facilities is $5,850,450... questions concerning this application may be directed to Glen DiEleuterio, Project Manager, at (302) 734...

75 FR 11168 - Dominion Transmission, Inc.; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-10

... units would be used (1) to compress inlet gas for the removal of natural gas liquids and (2) to compress... Commission's Regulations under the Natural Gas Act (NGA) as amended, to construct, install, own, operate, and maintain certain natural gas pipeline and compression facilities in Lewis County, West Virginia, under...

Experimental studies on tungsten-armour impact on nuclear responses of solid breeding blanket

NASA Astrophysics Data System (ADS)

Sato, Satoshi; Nakao, Makoto; Verzilov, Yury; Ochiai, Kentaro; Wada, Masayuki; Kubota, Naoyoshi; Kondo, Keitaro; Yamauchi, Michinori; Nishitani, Takeo

2005-07-01

In order to experimentally evaluate the tungsten armour impact on tritium production of the solid breeding blanket being developed by JAERI for tokamak-type DEMO reactors, neutronics integral experiments have been performed using DT neutrons at the Fusion Neutron Source facility of JAERI. Solid breeding blanket mockups relevant to the DEMO blanket have been applied in this study. The mockups are made of a set of layers consisting of 0-25.2 mm thick tungsten, 16 mm thick F82H, 12 mm thick Li2TiO3 and 100-200 mm thick beryllium with a cross-section of 660 × 660 mm in maximum. Pellets of Li2CO3 are embedded in the Li2TiO3 layers to measure the tritium production rate. By installing the 5 mm, 12.6 mm and 25.2 mm thick tungsten armours, the sum of the integrated tritium productions at the pellets are reduced by about 2.1%, 2.5% and 6.1% relative to the case without the armour, respectively. Numerical calculations have been conducted using the Monte Carlo code. In the case of the mockups with the tungsten armour, calculation results for the sum of the integrated tritium productions agree well with the experimental data within 4% and 19% in the experiments without and with a neutron reflector, respectively.

KSC-04pd1773

NASA Image and Video Library

2004-09-10

KENNEDY SPACE CENTER, FLA. - Members of a hurricane assessment team from Johnson Space Center and Marshall Space Flight Center observe the damage to the roof of the Thermal Protection System (TPS) Facility at KSC after Hurricane Frances hit the east coast of Central Florida and Kennedy Space Center. Near the center is astronaut Scott Altmann, a member of the team. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof. Equipment and materials that survived the storm have been relocated to the RLV hangar near the KSC Shuttle Landing Facility.

Impact penetration experiments in teflon targets of variable thickness

NASA Astrophysics Data System (ADS)

Hoerz, F.; Cintala, M. J.; Bernhard, R. P.; See, T. H.

1993-03-01

Approximately 20.4 sq m of Teflon thermal blankets on the nonspinning Long Duration Exposure Facility (LDEF) were exposed to the orbital debris and micrometeoroid environment in low-Earth orbit (LEO) for approximately 5.7 years. Each blanket consisted of an outer layer (approximately 125 micron thick) of FEP Teflon that was backed by a vapor-deposited metal mirror (Inconel; less than 1 micron thick). The inner surface consisted of organic binders and Chemglaze thermal protective paint (approximately 50 micron thick) resulting in a somewhat variable, total blanket thickness of approximately 180 to 200 microns. There was at least one of these blankets, each exposing approximately 1.2 sq m of surface area, on nine of LDEF's 12 principal pointing directions, the exceptions being Rows 3, 9, and 12. As a consequence, these blankets represent a significant opportunity for micrometeoroid and debris studies, in general, and specifically they provide an opportunity to address those issues that require information about pointing direction (i.e., spatial density of impact events as a function of instrument orientation). During deintegration of the LDEF spacecraft at KSC, all penetration holes greater than or equal to 300 micron in diameter were documented and were recently synthesized in terms of spatial density as a function of LDEF viewing direction by. The present report describes ongoing cratering and penetration experiments in pure Teflon targets, which are intended to establish the relationships between crater or penetration-hole diameters and the associated projectile dimensions at laboratory velocities (i.e., 6 km/s). The ultimate objective of these efforts is to extract reliable mass-frequencies and associated fluxes of hypervelocity particles in LEO.

KSC-2013-3251

NASA Image and Video Library

2013-08-09

CAPE CANAVERAL, Fla. – Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, technicians prepare a thermal blanket for installation on the MAVEN spacecraft's parabolic high gain antenna. MAVEN stands for Mars Atmosphere and Volatile Evolution. The antenna will communicate vast amounts of data to Earth during the mission. MAVEN is being prepared inside the facility for its scheduled November launch aboard a United Launch Alliance Atlas V rocket to Mars. Positioned in an orbit above the Red Planet, MAVEN will study the upper atmosphere of Mars in unprecedented detail. Photo credit: NASA/Jim Grossmann

KSC-2013-3255

NASA Image and Video Library

2013-08-09

CAPE CANAVERAL, Fla. – Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, technicians install a thermal blanket on the parabolic high gain antenna of the Mars Atmosphere and Volatile Evolution, or MAVEN spacecraft. The antenna will communicate vast amounts of data to Earth during the mission. MAVEN is being prepared inside the facility for its scheduled November launch aboard a United Launch Alliance Atlas V rocket to Mars. Positioned in an orbit above the Red Planet, MAVEN will study the upper atmosphere of Mars in unprecedented detail. Photo credit: NASA/Jim Grossmann

KSC-2013-3252

NASA Image and Video Library

2013-08-09

CAPE CANAVERAL, Fla. – Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, technicians apply tape to the thermal blanket for the MAVEN spacecraft's parabolic high gain antenna. MAVEN stands for Mars Atmosphere and Volatile Evolution. The antenna will communicate vast amounts of data to Earth during the mission. MAVEN is being prepared inside the facility for its scheduled November launch aboard a United Launch Alliance Atlas V rocket to Mars. Positioned in an orbit above the Red Planet, MAVEN will study the upper atmosphere of Mars in unprecedented detail. Photo credit: NASA/Jim Grossmann

76 FR 28972 - Eastern Shore Natural Gas Company; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2011-05-19

... project costs entirely from the Shippers, with no subsidy from Eastern Shore's other firm service customers. The total estimate cost of the proposed facilities is $13,018,853. Eastern Shore proposes the... directed to Glen DiEleuterio, Project Manager, at (302) 734-6710, ext. 6723 or via fax (302) 734-6745, or e...

75 FR 38093 - ConocoPhillips Alaska Natural Gas Corporation and Marathon Oil Company; Application for Blanket...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-01

... regasification terminal; and use of the existing terminal for exports to support the economic viability of a... LNG shipping at economic rates; and (3) strategic decisions regarding the future role of the Kenai LNG... Facility provides local economic benefits, including as an employer and as a source of royalties and taxes...

Space environmental effects on silvered Teflon thermal control surfaces

NASA Technical Reports Server (NTRS)

Hemminger, C. S.; Stuckey, W. K.; Uht, J. C.

1992-01-01

Cumulative space environmental effects on silver/fluorinated ethylene propylene (Ag/FEP) were a function of exposure orientation. Samples from nineteen silvered Teflon (Ag/FEP) thermal control surfaces recovered from the Long Duration Exposure Facility (LDEF) were analyzed to determine changes in this material as a function of position on the spacecraft. Although solar absorptance and infrared emittance of measured thermal blanket specimens are relatively unchanged from control specimen values, significant changes in surface morphology, composition, and chemistry were observed. We hypothesize that the FEP surfaces on the LDEF are degraded by UV radiation at all orientations, but that the damaged material has been removed by erosion from the blankets exposed to atomic oxygen flux and that contamination is masking the damage in some areas on the trays flanking the trailing edge.

KSC-98pc1160

NASA Image and Video Library

1998-09-27

KENNEDY SPACE CENTER, FLA. -- The Shuttle Carrier Aircraft with orbiter Atlantis on top touches down at the Shuttle Landing Facility. Atlantis returns home after a 10-month stay in the Palmdale, CA, orbiter processing facility undergoing extensive inspections and modifications. They included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. The flight from Palmdale included a fueling stop in Ft. Hood, TX, and overnight stay at Ft. Campbell, KY. Atlantis will undergo preparations in the Orbiter Processing Facility at KSC for its planned flight in June 1999

KSC-98pc1161

NASA Image and Video Library

1998-09-27

KENNEDY SPACE CENTER, FLA. -- The Shuttle Carrier Aircraft gently lands its piggyback cargo orbiter Atlantis at the Shuttle Landing Facility. Atlantis returns home after a 10-month stay in the Palmdale, CA, orbiter processing facility undergoing extensive inspections and modifications. They included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. The flight from Palmdale included a fueling stop in Ft. Hood, TX, and overnight stay at Ft. Campbell, KY. Atlantis will undergo preparations in the Orbiter Processing Facility at KSC for its planned flight in June 1999

KSC-98pc1159

NASA Image and Video Library

1998-09-27

KENNEDY SPACE CENTER, FLA. -- The Shuttle Carrier Aircraft with orbiter Atlantis on top arrives at the Shuttle Landing Facility. Atlantis returns home after a 10-month stay in the Palmdale, CA, orbiter processing facility undergoing extensive inspections and modifications. They included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. The flight from Palmdale included a fueling stop in Ft. Hood, TX, and overnight stay at Ft. Campbell, KY. Atlantis will undergo preparations in the Orbiter Processing Facility at KSC for its planned flight in June 1999

Space environment durability of beta cloth in LDEF thermal blankets

NASA Technical Reports Server (NTRS)

Linton, Roger C.; Whitaker, Ann F.; Finckenor, Miria M.

1993-01-01

Beta cloth performance for use on long-term space vehicles such as Space Station Freedom (S.S. Freedom) requires resistance to the degrading effects of the space environment. The major issues are retention of thermal insulating properties through maintaining optical properties, preserving mechanical integrity, and generating minimal particulates for contamination-sensitive spacecraft surfaces and payloads. The longest in-flight test of beta cloth's durability was on the Long Duration Exposure Facility (LDEF), where it was exposed to the space environment for 68 months. The LDEF contained 57 experiments which further defined the space environment and its effects on spacecraft materials. It was deployed into low-Earth orbit (LEO) in Apr. 1984 and retrieved Jan. 1990 by the space shuttle. Among the 10,000 plus material constituents and samples onboard were thermal control blankets of multilayer insulation with a beta cloth outer cover and Velcro attachments. These blankets were exposed to hard vacuum, thermal cycling, charged particles, meteoroid/debris impacts, ultraviolet (UV) radiation, and atomic oxygen (AO). Of these space environmental exposure elements, AO appears to have had the greatest effect on the beta cloth. The beta cloth analyzed in this report came from the MSFC Experiment S1005 (Transverse Flat-Plate Heat Pipe) tray oriented approximately 22 deg from the leading edge vector of the LDEF satellite. The location of the tray on LDEF and the placement of the beta cloth thermal blankets are shown. The specific space environment exposure conditions for this material are listed.

Present understanding of MHD and heat transfer phenomena for liquid metal blankets

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

Kirillov, I.R.; Barleon, L.; Reed, C.B.

1994-12-31

Liquid metals (Li, Li17Pb83, Pb) are considered as coolants in many designs of fusion reactor blankets. To estimate their potential and to make an optimal design, one has to know the magnetohydrodynamic (MHD) and heat transfer characteristics of liquid metal flow in the magnetic field. Such flows with high characteristic parameter values (Hartmann number M and interaction parameter N) open up a relatively new field in Magnetohydrodynamics requiring both theoretical and experimental efforts. A review of experimental work done for the last ten years in different countries shows that there are some data on MHD/HT characteristics in straight channels ofmore » simple geometry under fusion reactor relevant conditions (M>>1, N>>1) and not enough data for complex flow geometries. Future efforts should be directed to investigation of MHD/HT in straight channels with perfect and imperfect electroinsulated walls, including those with controlled imperfections, and in channels of complex geometry. The experiments are not simple, since the fusion relevant conditions require facilities with magnetic fields at, or even higher than, 5-7 T in comparatively large volumes. International cooperation in constructing and operating these facilities may be of great help.« less

Space Station WP-2 application of LDEF MLI results

NASA Technical Reports Server (NTRS)

Smith, Charles A.; Hasegawa, Mark M.; Jones, Cherie A.

1993-01-01

The Cascaded Variable Conductance Heat Pipe Experiment, which was developed by Michael Grote of McDonnell Douglas Electronic Systems Company, was located in Tray F-9 of the Long Duration Exposure Facility (LDEF), where it received atomic oxygen almost normal to its surface. The majority of the tray was covered by aluminized Kapton polyimide multilayer insulation (MLI), which showed substantial changes from atomic oxygen erosion. Most of the outermost Kapton layer of the MLI and the polyester scrim cloth under it were lost, and there was evidence of contaminant deposition which discolored the edges of the MLI blanket. Micrometeoroid and orbital debris (MM/OD) hits caused small rips in the MLI layers, and in some cases left cloudy areas where the vapor plume caused by a hit condensed on the next layer. The MLI was bent gradually through 90 deg at the edges to enclose the experiment, and the Kapton that survived along the curved portion showed the effects of atomic oxygen erosion at oblique angles. In spite of space environment effects over the period of the LDEF mission, the MLI blanket remained functional. The results of the analysis of LDEF MLI were used in developing the standard MLI blanket for Space Station Work Package-2 (WP-2). This blanket is expected to last 30 years when exposed to the low Earth orbit (LEO) environment constituents of atomic oxygen and MM/OD, which are the most damaging to MLI materials. The WP-2 standard blanket consists of an outer cover made from Beta-cloth glass fiber fabric which is aluminized on the interior surface, and an inner cover of 0.076-mm (0.003-in) double-side-aluminized perforated Kapton. The inner reflector layers are 0.0076-mm (0.0003-in) double-side aluminized, perforated Kapton separated by layers of Dacron polyester fabric. The outer cover was selected to be resistant to the LEO environment and durable enough to survive in orbit for 30 years. This paper describes the analyses of the LDEF MLI results, and how these results contributed to the selection of the WP-2 MLI blanket materials and configuration.

Nonterrestrial material processing and manufacturing of large space systems

NASA Technical Reports Server (NTRS)

Von Tiesenhausen, G.

1979-01-01

Nonterrestrial processing of materials and manufacturing of large space system components from preprocessed lunar materials at a manufacturing site in space is described. Lunar materials mined and preprocessed at the lunar resource complex will be flown to the space manufacturing facility (SMF), where together with supplementary terrestrial materials, they will be final processed and fabricated into space communication systems, solar cell blankets, radio frequency generators, and electrical equipment. Satellite Power System (SPS) material requirements and lunar material availability and utilization are detailed, and the SMF processing, refining, fabricating facilities, material flow and manpower requirements are described.

The LBM program at the EPFL/LOTUS Facility

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

File, J.; Jassby, D.L.; Tsang, F.Y.

1986-11-01

An experimental program of neutron transport studies of the Lithium Blanket Module (LBM) is being carried out with the LOTUS point-neutron source facility at Ecole Polytechnique Federale de Lausanne (EPFL), Switzerland. Preliminary experiments use passive neutron dosimetry within the fuel rods in the LBM central zone, as well as, both thermal extraction and dissolution methods to assay tritium bred in Li/sub 2/O diagnostic wafers and LBM pellets. These measurements are being compared and reconciled with each other and with the predictions of two-dimensional discrete-ordinates and continuous-energy Monte-Carlo analyses of the Lotus/LBM system.

Communication satellites for STS-5 being readied for loading

NASA Technical Reports Server (NTRS)

1982-01-01

Two commercial communication satellites scheduled for flight on STS-5 are pictured as they are being readied for loading into a special canister that will transport them to the launch pad. Telsat Canada's Anik C-3 (at bottom) is seen in its blanket covered cradle assemble. Satellite Business System's SBS-3 is at top. This photo was taken inside the vertical processing facility (VPF).

KSC-98pc1162

NASA Image and Video Library

1998-09-27

KENNEDY SPACE CENTER, FLA. -- The Shuttle Carrier Aircraft rolls to a stop with its piggyback cargo orbiter Atlantis at the Shuttle Landing Facility. In the background is the Vehicle Assembly Building. Atlantis returns home after a 10-month stay in the Palmdale, CA, orbiter processing facility undergoing extensive inspections and modifications. They included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. The flight from Palmdale included a fueling stop in Ft. Hood, TX, and overnight stay at Ft. Campbell, KY. Atlantis will undergo preparations in the Orbiter Processing Facility at KSC for its planned flight in June 1999

KSC-98pc1163

NASA Image and Video Library

1998-09-27

KENNEDY SPACE CENTER, FLA. -- Stairs are rolled to the forward opening of the Shuttle Carrier Aircraft with its piggyback cargo, the orbiter Atlantis after it rolls to a stop at the Shuttle Landing Facility. Atlantis returns home after a 10-month stay in the Palmdale, CA, orbiter processing facility undergoing extensive inspections and modifications. They included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. The flight from Palmdale included a fueling stop in Ft. Hood, TX, and overnight stay at Ft. Campbell, KY. Atlantis will undergo preparations in the Orbiter Processing Facility at KSC for its planned flight in June 1999

KSC-04pd1775

NASA Image and Video Library

2004-09-10

KENNEDY SPACE CENTER, FLA. - Members of a hurricane assessment team from Johnson Space Center and Marshall Space Flight Center observe the damage to the roof of the Thermal Protection System (TPS) Facility at KSC after Hurricane Frances hit the east coast of Central Florida and Kennedy Space Center. At left is astronaut Scott Altmann, a member of the team, and at center is Martin Wilson, manager of the TPS operations. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof. Equipment and materials that survived the storm have been relocated to the RLV hangar near the KSC Shuttle Landing Facility.

IADC Vulnerability Report, IT32-21

NASA Technical Reports Server (NTRS)

Christiansen, E. L.; Miller, J. E.; Hyde, J.

2016-01-01

Numerous mission support hardware systems and their spares are maintained outside of the habitable volume of the International Space Station (ISS), and are arranged covered by a multi-layer insulation (MLI) thermal blanket which provides both thermal control and a measure of protection from micrometeoroids and orbital debris (MMOD). The NASA Hypervelocity Impact Technology (HVIT) group at the Johnson Space Center in Houston Texas has assessed the protection provided by MLI in a series of hypervelocity impact tests using a 1 mm thick aluminum 6061-T6 rear wall to simulate the actual hardware behind the MLI. HVIT has also evaluated methods to enhance the protection provided by MLI thermal blankets. The impact study used both aluminum and steel spherical projectiles accelerated to speeds of 7 km/s using a 4.3 mm, two-stage, light-gas gun at the NASA White Sands Test Facility (WSTF).

Radiative-conductive inverse problem for lumped parameter systems

NASA Astrophysics Data System (ADS)

Alifanov, O. M.; Nenarokomov, A. V.; Gonzalez, V. M.

2008-11-01

The purpose of this paper is to introduce a iterative regularization method in the research of radiative and thermal properties of materials with applications in the design of Thermal Control Systems (TCS) of spacecrafts. In this paper the radiative and thermal properties (emissivity and thermal conductance) of a multilayered thermal-insulating blanket (MLI), which is a screen-vacuum thermal insulation as a part of the (TCS) for perspective spacecrafts, are estimated. Properties of the materials under study are determined in the result of temperature and heat flux measurement data processing based on the solution of the Inverse Heat Transfer Problem (IHTP) technique. Given are physical and mathematical models of heat transfer processes in a specimen of the multilayered thermal-insulating blanket located in the experimental facility. A mathematical formulation of the inverse heat conduction problem is presented too. The practical testing were performed for specimen of the real MLI.

ASCANS Class of 2013 Tour

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. -- In the Thermal Protection System Facility NASA's Kennedy Space Center in Florida, agency astronaut candidates are briefed on thermal blankets being manufactured for agency spacecraft. Looking at sample thermal blankets are, from the left, Nicole Mann, Andrew Morgan, Christina Hammock, Josh Cassada, Jessica Meir, Tyler ‘Nick’ Hague, and Anne McClain. Plans call for the Lockheed Martin-built Orion to launch atop a United Launch Alliance Delta IV Heavy rocket from Cape Canaveral Air Force Station on Exploration Flight Test EFT-1 later this year. The astronaut class of 2013 was selected by NASA after an extensive year-and-a-half search. The new group will help the agency push the boundaries of exploration and travel to new destinations in the solar system. To learn more about the astronaut class of 2013, visit: http://www.nasa.gov/astronauts/2013astroclass.html Photo credit: NASA/Kim Shiflett

Study of multilayer thermal insulation by inverse problems method

NASA Astrophysics Data System (ADS)

Alifanov, O. M.; Nenarokomov, A. V.; Gonzalez, V. M.

2009-11-01

The purpose of this paper is to introduce a new method in the research of radiative and thermal properties of materials with further applications in the design of thermal control systems (TCS) of spacecrafts. In this paper the radiative and thermal properties (emissivity and thermal conductance) of a multilayered thermal-insulating blanket (MLI), which is a screen-vacuum thermal insulation as a part of the TCS for perspective spacecrafts, are estimated. Properties of the materials under study are determined in the result of temperature and heat flux measurement data processing based on the solution of the inverse heat transfer problem (IHTP) technique. Given are physical and mathematical models of heat transfer processes in a specimen of the multilayered thermal-insulating blanket located in the experimental facility. A mathematical formulation of the inverse heat conduction problem is presented as well. The practical approves were made for specimen of the real MLI.

Multipurpose hardened spacecraft insulation

NASA Technical Reports Server (NTRS)

Steimer, Carlos H.

1990-01-01

A Multipurpose Hardened Spacecraft Multilayer Insulation (MLI) system was developed and implemented to meet diverse survivability and performance requirements. Within the definition and confines of a MLI assembly (blanket), the design: (1) provides environmental protection from natural and induced nuclear, thermal, and electromagnetic radiation; (2) provides adequate electrostatic discharge protection for a geosynchronous satellite; (3) provides adequate shielding to meet radiated emission needs; and (4) will survive ascent differential pressure loads between enclosed volume and space. The MLI design is described which meets these requirements and design evolution and verification is discussed. The application is for MLI blankets which closeout the area between the laser crosslink subsystem (LCS) equipment and the DSP spacecraft cabin. Ancillary needs were implemented to ease installation at launch facility and to survive ascent acoustic and vibration loads. Directional venting accommodations were also incorporated to avoid contamination of LCS telescope, spacecraft sensors, and second surface mirrors (SSMs).

Tritium assay of Li/sub 2/O in the LBM/LOTUS experiments

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

Quanci, J.; Azam, S.; Bertone, P.

1986-11-01

The Lithium Blanket Module (LBM) is an assembly of over 20,000 cylindrical lithium oxide pellets in an array representative of a limited-coverage breeding zone for a toroidal fusion device. A principal objective of the LBM program is to test the ability of advanced neutronics coding to model the tritium breeding characteristics of a fusion device blanket. The LBM has been irradiated at the Ecole Polytechnique Federale de Lausanne (EPFL) LOTUS facility with a 14 MeV point-neutron source. Princeton Plasma Physics Laboratory (PPPL) and EPFL assayed the tritium bred in lithium oxide diagnostic samples placed at various positions in the LBM.more » PPPL employed a thermal extraction technique while EPFL used a dissolution method. The results for the assay are reported and compared to MCNP Monte Carlo neutronics calculations for the LBM/LOTUS system.« less

Neutronics Evaluation of Lithium-Based Ternary Alloys in IFE Blankets

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

Jolodosky, A.; Fratoni, M.

2014-11-20

Pre-conceptual fusion blanket designs require research and development to reflect important proposed changes in the design of essential systems, and the new challenges they impose on related fuel cycle systems. One attractive feature of using liquid lithium as the breeder and coolant is that it has very high tritium solubility and results in very low levels of tritium permeation throughout the facility infrastructure. However, lithium metal vigorously reacts with air and water and presents plant safety concerns. If the chemical reactivity of lithium could be overcome, the result would have a profound impact on fusion energy and associated safety basis.more » The overriding goal of this project is to develop a lithium-based alloy that maintains beneficial properties of lithium (e.g. high tritium breeding and solubility) while reducing overall flammability concerns. To minimize the number of alloy combinations that must be explored, only those alloys that meet certain nuclear performance metrics will be considered for subsequent thermodynamic study. The specific scope of this study is to evaluate the neutronics performance of lithium-based alloys in the blanket of an inertial confinement fusion (ICF) engine. The results of this study will inform the development of lithium alloys that would guarantee acceptable neutronics performance while mitigating the chemical reactivity issues of pure lithium.« less

47 CFR 25.226 - Blanket licensing provisions for domestic, U.S. Vehicle-Mounted Earth Stations (VMESs) receiving...

Code of Federal Regulations, 2010 CFR

2010-10-01

... of VMESs in the 14.47-14.5 GHz (Earth-to-space) frequency band in the vicinity of radio astronomy... location, and the applicable coordination zone. Table 1—Applicable Radio Astronomy Service (RAS) Facilities... Astronomical Research Institute, Rosman, NC 35°11′59″ 82°52′19″ 160. U of Michigan Radio Astronomy Observatory...

47 CFR 25.226 - Blanket licensing provisions for domestic, U.S. Vehicle-Mounted Earth Stations (VMESs) receiving...

Code of Federal Regulations, 2012 CFR

2012-10-01

... of VMESs in the 14.47-14.5 GHz (Earth-to-space) frequency band in the vicinity of radio astronomy... location, and the applicable coordination zone. Table 1—Applicable Radio Astronomy Service (RAS) Facilities... Astronomical Research Institute, Rosman, NC 35°11′59″ 82°52′19″ 160. U of Michigan Radio Astronomy Observatory...

47 CFR 25.226 - Blanket Licensing provisions for domestic, U.S. Vehicle-Mounted Earth Stations (VMESs) receiving...

Code of Federal Regulations, 2014 CFR

2014-10-01

... in the 14.47-14.5 GHz (Earth-to-space) frequency band in the vicinity of radio astronomy service (RAS... coordination zone. Table 1—Applicable Radio Astronomy Service (RAS) Facilities and Associated Coordination..., Rosman, NC 35°11′59″ 82°52′19″ 160. U of Michigan Radio Astronomy Observatory, Stinchfield Woods, MI 42...

47 CFR 25.226 - Blanket licensing provisions for domestic, U.S. Vehicle-Mounted Earth Stations (VMESs) receiving...

Code of Federal Regulations, 2011 CFR

2011-10-01

... of VMESs in the 14.47-14.5 GHz (Earth-to-space) frequency band in the vicinity of radio astronomy... location, and the applicable coordination zone. Table 1—Applicable Radio Astronomy Service (RAS) Facilities... Astronomical Research Institute, Rosman, NC 35°11′59″ 82°52′19″ 160. U of Michigan Radio Astronomy Observatory...

KSC-04pd0705

NASA Image and Video Library

2004-04-05

KENNEDY SPACE CENTER, FLA. -- United Space Alliance (USA) technicians Mike Williams (left) and R. Justin Hopmann (right) lift the thermal blanket insulation into Discovery’s nose cap, which is under a protective cover and seated above them on a work stand. The work is being done in a low bay area outside the Orbiter Processing Facility. Discovery is the orbiter named as the vehicle for Return to Flight with mission STS-114.

Fabrication and integrity test preparation of HIP-joined W and ferritic-martensitic steel mockups for fusion reactor development

NASA Astrophysics Data System (ADS)

Lee, Dong Won; Shin, Kyu In; Kim, Suk Kwon; Jin, Hyung Gon; Lee, Eo Hwak; Yoon, Jae Sung; Choi, Bo Guen; Moon, Se Youn; Hong, Bong Guen

2014-10-01

Tungsten (W) and ferritic-martensitic steel (FMS) as armor and structural materials, respectively, are the major candidates for plasma-facing components (PFCs) such as the blanket first wall (BFW) and the divertor, in a fusion reactor. In the present study, three W/FMS mockups were successfully fabricated using a hot isostatic pressing (HIP, 900 °C, 100 MPa, 1.5 hrs) with a following post-HIP heat treatment (PHHT, tempering, 750 °C, 70 MPa, 2 hrs), and the W/FMS joining method was developed based on the ITER BFW and the test blanket module (TBM) development project from 2004 to the present. Using a 10-MHz-frequency flat-type probe to ultrasonically test of the joint, we found no defects in the fabricated mockups. For confirmation of the joint integrity, a high heat flux test will be performed up to the thermal lifetime of the mockup under the proper test conditions. These conditions were determined through a preliminary analysis with conventional codes such as ANSYS-CFX for thermal-hydraulic conditions considering the test facility, the Korea heat load test facility with an electron beam (KoHLT-EB), and its water coolant system at the Korea Atomic Energy Research Institute (KAERI).

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, NASA’s MESSENGER spacecraft is secure after transfer to the work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, NASA’s MESSENGER spacecraft is secure after transfer to the work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, NASA’s MESSENGER spacecraft is lifted off the pallet for transfer to a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, NASA’s MESSENGER spacecraft is lifted off the pallet for transfer to a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers remove the protective cover from NASA’s MESSENGER spacecraft. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers remove the protective cover from NASA’s MESSENGER spacecraft. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, workers check the placement of NASA’s MESSENGER spacecraft on a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, workers check the placement of NASA’s MESSENGER spacecraft on a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, workers move NASA’s MESSENGER spacecraft into a high bay clean room. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, workers move NASA’s MESSENGER spacecraft into a high bay clean room. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, an overhead crane moves NASA’s MESSENGER spacecraft toward a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, an overhead crane moves NASA’s MESSENGER spacecraft toward a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, an overhead crane lowers NASA’s MESSENGER spacecraft onto a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities, an overhead crane lowers NASA’s MESSENGER spacecraft onto a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, NASA’s MESSENGER spacecraft is revealed. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, NASA’s MESSENGER spacecraft is revealed. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

Blanket design and optimization demonstrations of the first wall/blanket/shield design and optimization system (BSDOS).

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

Gohar, Y.; Nuclear Engineering Division

2005-05-01

In fusion reactors, the blanket design and its characteristics have a major impact on the reactor performance, size, and economics. The selection and arrangement of the blanket materials, dimensions of the different blanket zones, and different requirements of the selected materials for a satisfactory performance are the main parameters, which define the blanket performance. These parameters translate to a large number of variables and design constraints, which need to be simultaneously considered in the blanket design process. This represents a major design challenge because of the lack of a comprehensive design tool capable of considering all these variables to definemore » the optimum blanket design and satisfying all the design constraints for the adopted figure of merit and the blanket design criteria. The blanket design capabilities of the First Wall/Blanket/Shield Design and Optimization System (BSDOS) have been developed to overcome this difficulty and to provide the state-of-the-art research and design tool for performing blanket design analyses. This paper describes some of the BSDOS capabilities and demonstrates its use. In addition, the use of the optimization capability of the BSDOS can result in a significant blanket performance enhancement and cost saving for the reactor design under consideration. In this paper, examples are presented, which utilize an earlier version of the ITER solid breeder blanket design and a high power density self-cooled lithium blanket design for demonstrating some of the BSDOS blanket design capabilities.« less

Blanket Design and Optimization Demonstrations of the First Wall/Blanket/Shield Design and Optimization System (BSDOS)

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

Gohar, Yousry

2005-05-15

In fusion reactors, the blanket design and its characteristics have a major impact on the reactor performance, size, and economics. The selection and arrangement of the blanket materials, dimensions of the different blanket zones, and different requirements of the selected materials for a satisfactory performance are the main parameters, which define the blanket performance. These parameters translate to a large number of variables and design constraints, which need to be simultaneously considered in the blanket design process. This represents a major design challenge because of the lack of a comprehensive design tool capable of considering all these variables to definemore » the optimum blanket design and satisfying all the design constraints for the adopted figure of merit and the blanket design criteria. The blanket design capabilities of the First Wall/Blanket/Shield Design and Optimization System (BSDOS) have been developed to overcome this difficulty and to provide the state-of-the-art research and design tool for performing blanket design analyses. This paper describes some of the BSDOS capabilities and demonstrates its use. In addition, the use of the optimization capability of the BSDOS can result in a significant blanket performance enhancement and cost saving for the reactor design under consideration. In this paper, examples are presented, which utilize an earlier version of the ITER solid breeder blanket design and a high power density self-cooled lithium blanket design for demonstrating some of the BSDOS blanket design capabilities.« less

Savannah River Plant engineering and design history. Volume 4: 300/700 Areas & general services and facilities

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

Not Available

1957-01-01

The primary function of the 300 Area is the production and preparation of the fuel and target elements required for the 100 Area production reactors. Uranium slugs and lithium-aluminium alloy control and blanket rods are prepared in separate structures. Other facilities include a test pile, a physics assembly laboratory, an office and change house, an electrical substation, and various service facilities such as rail lines, roads, sewers, steam and water distribution lines, etc. The 700 Area contains housing and facilities for plant management, general plant services, and certain technical activities. The technical buildings include the Main Technical Laboratory, the Wastemore » Concentration Building, the Health Physics Headquarters, and the Health Physics Calibration building. Sections of this report describe the following: development of the 300-M Area; selection and description of process; design of main facilities of the 300 Area; development of the 700-A Area; design of the main facilities of the 700 Area; and general services and facilities, including transportation, plant protection, waste disposal and drainage, site work, pilot plants, storage, and furniture and fixtures.« less

KSC-04pd0704

NASA Image and Video Library

2004-04-05

KENNEDY SPACE CENTER, FLA. -- United Space Alliance (USA) technicians Mike Williams (left), Pearl Richardson (center) and R. Justin Hopmann get ready to lift the thermal blanket insulation into Discovery’s nose cap, which is under a protective cover and seated above on a work stand. The work is being done in a low bay area outside the Orbiter Processing Facility. Discovery is the orbiter named as the vehicle for Return to Flight with mission STS-114.

KSC-03pd0326

NASA Image and Video Library

2003-02-07

KENNEDY SPACE CENTER, FLA. -- In the Thermal Protection System Facility, NASA Administrator Sean O'Keefe looks at a Dome Heat Shield blanket that is used for Shuttle engines. O'Keefe is visiting the site to learn more about the TPS products and process in protecting orbiters from the intense heat of launch and re-entry. TPS tiles have been discussed in the investigation into the Columbia tragedy that destroyed the orbiter and claimed the lives of seven astronauts.

KSC-98pc1167

NASA Image and Video Library

1998-09-28

Seen from behind, the orbiter Atlantis approaches the entrance of Orbiter Processing Facility 2 (OPF-2) where it will undergo preparations for its planned flight in June 1999. Atlantis spent 10 months in Palmdale, CA, undergoing extensive inspections and modifications in the orbiter processing facility there. The modifications included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. OPF-2 consists of a 2,700-square-meter (29,000 square ft.) high bay. The building measures 29 meters (95 ft). high, 121 meters (397 ft.) long and 71 meters (233 ft.) wide

KSC-98pc1168

NASA Image and Video Library

1998-09-28

Seen from behind, the orbiter Atlantis moves into the Orbiter Processing Facility 2 (OPF-2) where it will undergo preparations for its planned flight in June 1999. Atlantis spent 10 months in Palmdale, CA, undergoing extensive inspections and modifications in the orbiter processing facility there. The modifications included several upgrades enabling it to support International Space Station missions, such as adding an external airlock for ISS docking missions and installing thinner, lighter thermal protection blankets for weight reduction which will allow it to haul heavier cargo. OPF-2 consists of two 2,700-square-meter (29,000 square feet) high bays. It measures 29 meters (95 ft). high, 121 meters (397 ft) long and 71 meters (233 ft) wide

How to improve the irradiation conditions for the International Fusion Materials Irradiation Facility

NASA Astrophysics Data System (ADS)

Daum, Eric

2000-12-01

The accelerator-based intense D-Li neutron source International Fusion Materials Irradiation Facility (IFMIF) provides very suitable irradiation conditions for fusion materials development with the attractive option of accelerated irradiations. Investigations show that a neutron moderator made of tungsten and placed in the IFMIF test cell can further improve the irradiation conditions. The moderator softens the IFMIF neutron spectrum by enhancing the fraction of low energy neutrons. For displacement damage, the ratio of point defects to cascades is more DEMO relevant and for tritium production in Li-based breeding ceramic materials it leads to a preferred production via the 6Li(n,t) 4He channel as it occurs in a DEMO breeding blanket.

Analysis of selected materials flown on interior locations of the Long Duration Exposure Facility

NASA Technical Reports Server (NTRS)

Smith, H. A.; Nelson, K. M.; Eash, D.; Pippin, H. G.

1994-01-01

This report documents the post-flight condition of selected hardware taken from interior locations on the Long Duration Exposure Facility (LDEF). This hardware was generally in excellent condition. Outgassing data is presented for heat shrink tubing and fiberglass composite shims. Variation in total mass loss (TML) values for heat shrink tubing were correlated with location. Nylon grommets were evaluated for mechanical integrity; slight embrittlement was observed for flight specimens. Multi-layer insulation blankets, wire bundles, and paints in non-exposed interior locations were all in visibly good condition. Silicon-containing contaminant films were observed on silver-coated hex nuts at the space- and Earth-end interior locations.

Characterizing shallow secondary clarifier performance where conventional flux theory over-estimates allowable solids loading rate.

PubMed

Daigger, Glen T; Siczka, John S; Smith, Thomas F; Frank, David A; McCorquodale, J A

The performance characteristics of relatively shallow (3.3 and 3.7 m sidewater depth in 30.5 m diameter) activated sludge secondary clarifiers were extensively evaluated during a 2-year testing program at the City of Akron Water Reclamation Facility (WRF), Ohio, USA. Testing included hydraulic and solids loading stress tests, and measurement of sludge characteristics (zone settling velocity (ZSV), dispersed and flocculated total suspended solids), and the results were used to calibrate computational fluid dynamic (CFD) models of the various clarifiers tested. The results demonstrated that good performance could be sustained at surface overflow rates in excess of 3 m/h, as long as the clarifier influent mixed liquor suspended solids (MLSS) concentration was controlled to below critical values. The limiting solids loading rate (SLR) was significantly lower than the value predicted by conventional solids flux analysis based on the measured ZSV/MLSS relationship. CFD analysis suggested that this resulted because mixed liquor entering the clarifier was being directed into the settled sludge blanket, diluting it and also creating a 'thin' concentration sludge blanket that overlays the thicker concentration sludge blanket typically expected. These results indicate the need to determine the allowable SLR for shallow clarifiers using approaches other than traditional solids flux analysis. A combination of actual testing and CFD analyses are demonstrated here to be effective in doing so.

KSC-08pd2290

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment (MULE) carrier is driven from the Canister Rotation Facility to the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center after the shipping container was pressure cleaned. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

Improved multilayer insulation applications. [spacecraft thermal control

NASA Technical Reports Server (NTRS)

Mikk, G.

1982-01-01

Multilayer insulation blankets used for the attenuation of radiant heat transfer in spacecraft are addressed. Typically, blanket effectiveness is degraded by heat leaks in the joints between adjacent blankets and by heat leaks caused by the blanket fastener system. An approach to blanket design based upon modular sub-blankets with distributed seams and upon an associated fastener system that practically eliminates the through-the-blanket conductive path is described. Test results are discussed providing confirmation of the approach. The specific case of the thermal control system for the optical assembly of the Space Telescope is examined.

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers prepare NASA’s MESSENGER spacecraft for transfer to a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers prepare NASA’s MESSENGER spacecraft for transfer to a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, workers begin moving NASA’s MESSENGER spacecraft into the building MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - is being taken into a high bay clean room where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, workers begin moving NASA’s MESSENGER spacecraft into the building MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - is being taken into a high bay clean room where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, a lift begins lowering NASA’s MESSENGER spacecraft onto the ground. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, a lift begins lowering NASA’s MESSENGER spacecraft onto the ground. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers get ready to remove the protective cover from NASA’s MESSENGER spacecraft. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers get ready to remove the protective cover from NASA’s MESSENGER spacecraft. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, workers check the moveable pallet holding NASA’s MESSENGER spacecraft. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, workers check the moveable pallet holding NASA’s MESSENGER spacecraft. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

LDEF data correlation to existing NASA debris environment models

NASA Technical Reports Server (NTRS)

Atkinson, Dale R.; Allbrooks, Martha K.; Watts, Alan J.

1992-01-01

The Long Duration Exposure Facility (LDEF) was recovered in January 1990, following 5.75 years exposure of about 130 sq. m to low-Earth orbit. About 25 sq. m of this surface area was aluminum 6061 T-6 exposed in every direction. In addition, about 17 sq. m of Scheldahl G411500 silver-Teflon thermal control blankets were exposed in 9 of the 12 directions. Since the LDEF was gravity gradient stabilized and did not rotate, the directional dependence of the flux can be easily distinguished. During the disintegration of the LDEF, all impact features larger than 0.5 mm into aluminum were documented for diameters and locations. In addition, the diameters and locations of all impact features larger than 0.3 mm into Scheldahl G411500 thermal control blankets were also documented. This data, along with additional information collected from LDEF materials will be compared with current meteoroid and debris models. This comparison will provide a validation of the models and will identify discrepancies between the models and the data.

Parameter Identification Of Multilayer Thermal Insulation By Inverse Problems

NASA Astrophysics Data System (ADS)

Nenarokomov, Aleksey V.; Alifanov, Oleg M.; Gonzalez, Vivaldo M.

2012-07-01

The purpose of this paper is to introduce an iterative regularization method in the research of radiative and thermal properties of materials with further applications in the design of Thermal Control Systems (TCS) of spacecrafts. In this paper the radiative and thermal properties (heat capacity, emissivity and thermal conductance) of a multilayered thermal-insulating blanket (MLI), which is a screen-vacuum thermal insulation as a part of the (TCS) for perspective spacecrafts, are estimated. Properties of the materials under study are determined in the result of temperature and heat flux measurement data processing based on the solution of the Inverse Heat Transfer Problem (IHTP) technique. Given are physical and mathematical models of heat transfer processes in a specimen of the multilayered thermal-insulating blanket located in the experimental facility. A mathematical formulation of the IHTP, based on sensitivity function approach, is presented too. The practical testing was performed for specimen of the real MLI. This paper consists of recent researches, which developed the approach suggested at [1].

75 FR 50991 - Antidumping Duty Order: Certain Woven Electric Blankets From the People's Republic of China

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-18

...: Certain Woven Electric Blankets From the People's Republic of China AGENCY: Import Administration... electric blankets (``woven electric blankets'') from the People's Republic of China (``PRC''). FOR FURTHER... Certain Woven Electric Blankets From the People's Republic of China: Final Determination of Sales at Less...

A Fusion Nuclear Science Facility for a fast-track path to DEMO

DOE PAGES

Garofalo, Andrea M.; Abdou, M.; Canik, John M.; ...

2014-10-01

An accelerated fusion energy development program, a “fast-track” approach, requires developing an understanding of fusion nuclear science (FNS) in parallel with research on ITER to study burning plasmas. A Fusion Nuclear Science Facility (FNSF) in parallel with ITER provides the capability to resolve FNS feasibility issues related to power extraction, tritium fuel sustainability, and reliability, and to begin construction of DEMO upon the achievement of Q~10 in ITER. Fusion nuclear components, including the first wall (FW)/blanket, divertor, heating/fueling systems, etc. are complex systems with many inter-related functions and different materials, fluids, and physical interfaces. These in-vessel nuclear components must operatemore » continuously and reliably with: (a) Plasma exposure, surface particle & radiation loads, (b) High energy 2 neutron fluxes and their interactions in materials (e.g. peaked volumetric heating with steep gradients, tritium production, activation, atomic displacements, gas production, etc.), (c) Strong magnetic fields with temporal and spatial variations (electromagnetic coupling to the plasma including off-normal events like disruptions), and (d) a High temperature, high vacuum, chemically active environment. While many of these conditions and effects are being studied with separate and multiple effect experimental test stands and modeling, fusion nuclear conditions cannot be completely simulated outside the fusion environment. This means there are many new multi-physics, multi-scale phenomena and synergistic effects yet to be discovered and accounted for in the understanding, design and operation of fusion as a self-sustaining, energy producing system, and significant experimentation and operational experience in a true fusion environment is an essential requirement. In the following sections we discuss the FNSF objectives, describe the facility requirements and a facility concept and operation approach that can accomplish those objectives, and assess the readiness to construct with respect to several key FNSF issues: materials, steady-state operation, disruptions, power exhaust, and breeding blanket. Finally we present our conclusions.« less

Study on the temperature control mechanism of the tritium breeding blanket for CFETR

NASA Astrophysics Data System (ADS)

Liu, Changle; Qiu, Yang; Zhang, Jie; Zhang, Jianzhong; Li, Lei; Yao, Damao; Li, Guoqiang; Gao, Xiang; Wu, Songtao; Wan, Yuanxi

2017-12-01

The Chinese fusion engineering testing reactor (CFETR) will demonstrate tritium self- sufficiency using a tritium breeding blanket for the tritium fuel cycle. The temperature control mechanism (TCM) involves the tritium production of the breeding blanket and has an impact on tritium self-sufficiency. In this letter, the CFETR tritium target is addressed according to its missions. TCM research on the neutronics and thermal hydraulics issues for the CFETR blanket is presented. The key concerns regarding the blanket design for tritium production under temperature field control are depicted. A systematic theory on the TCM is established based on a multiplier blanket model. In particular, a closed-loop method is developed for the mechanism with universal function solutions, which is employed in the CFETR blanket design activity for tritium production. A tritium accumulation phenomenon is found close to the coolant in the blanket interior, which has a very important impact on current blanket concepts using water coolant inside the blanket. In addition, an optimal tritium breeding ratio (TBR) method based on the TCM is proposed, combined with thermal hydraulics and finite element technology. Meanwhile, the energy gain factor is adopted to estimate neutron heat deposition, which is a key parameter relating to the blanket TBR calculations, considering the structural factors. This work will benefit breeding blanket engineering for the CFETR reactor in the future.

75 FR 46911 - Certain Woven Electric Blankets from the People's Republic of China: Amended Final Determination...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-04

... Blankets from the People's Republic of China: Amended Final Determination of Sales at Less Than Fair Value... than fair value (``LTFV'') in the antidumping investigation of certain woven electric blankets (``woven electric blankets'') from the People's Republic of China (``PRC''). See Certain Woven Electric Blankets...

Effect of processing parameters and pore structure of nanostructured silica aerogel on the physical properties of aerogel blankets

NASA Astrophysics Data System (ADS)

Latifi, Fatemeh; Talebi, Zahra; Khalili, Haleh; Zarrebini, Mohammad

2018-05-01

This work investigates the influence of processing parameters and aerogel pore structure on the physical properties and hydrophobicity of aerogel blankets. Aerogel blankets were produced by in situ synthesis of nanostructured silica aerogel on a polyester nonwoven substrate. Nitrogen adsorption-desorption analysis, contact angle test and FE-SEM images were used to characterize both the aerogel particles and the blankets. The results showed that the weight and thickness of the blanket were reduced when the low amount of catalyst was used. A decrease in the aerogel pore size from 22 to 11 nm increased the weight and thickness of the blankets. The xerogel particles with high density and pore size of 5 nm reduced the blanket weight. Also, the blanket weight and thickness were increased due to increasing the sol volume. It was found that the hydrophobicity of aerogel blankets is not influenced by sol volume and pore structure of silica aerogel.

Fusion reactor blanket/shield design study

NASA Astrophysics Data System (ADS)

Smith, D. L.; Clemmer, R. G.; Harkness, S. D.; Jung, J.; Krazinski, J. L.; Mattas, R. F.; Stevens, H. C.; Youngdahl, C. K.; Trachsel, C.; Bowers, D.

1979-07-01

A joint study of Tokamak reactor first wall/blanket/shield technology was conducted to identify key technological limitations for various tritium breeding blanket design concepts, establishment of a basis for assessment and comparison of the design features of each concept, and development of optimized blanket designs. The approach used involved a review of previously proposed blanket designs, analysis of critical technological problems and design features associated with each of the blanket concepts, and a detailed evaluation of the most tractable design concepts. Tritium breeding blanket concepts were evaluated according to the proposed coolant. The effort concentrated on evaluation of lithium and water cooled blanket designs and helium and molten salt cooled designs. Generalized nuclear analysis of the tritium breeding performance, an analysis of tritium breeding requirements, and a first wall stress analysis were conducted as part of the study. The impact of coolant selection on the mechanical design of a Tokamak reactor was evaluated. Reference blanket designs utilizing the four candidate coolants are presented.

Measurement of Radiation Protection Factors for Contaminated Vehicles

DTIC Science & Technology

1999-03-01

sources, developed by the Aberdeen Test Center in the USA. Point sources of 6°Co are embedded in a blanket (on a 0.5 m grid) and draped over a vehicle...constructing a similar facility. Thus, a different approach is desired. This is achieved through the arrangement depicted in Figure 1. A rubber tube is draped ...Figure 1: Experimental set-up. A rubber tube was draped over the Grizzly at one foot intervals along the side ofthe Grizzly. Two motors (one shown at

KSC-04pd1902

NASA Image and Video Library

2004-09-22

KENNEDY SPACE CENTER, FLA. - Workers attempt to secure the roof of the Tile Shop in the Thermal Protection System Facility (TPSF) in preparation for Hurricane Jeanne, which is expected to impact Central Florida Sunday. The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, lost approximately 35 percent of its roof during Hurricane Frances, which blew across Central Florida Sept. 4. Jeanne is the fourth hurricane in 45 days to make landfall somewhere in the state.

Extremely Low Frequency (ELF) Vertical Electric Field Exposure of Rats: Irradiation Facility

DTIC Science & Technology

1977-05-01

altered inside an animal cage even with wet or dry litter and full food and water containers. Rats weighing approximately 300 g in adjacent cages caused...with guard circuit Field inside empty cage Field inside complete cage ( litter (wet or dry) + food + water) Field variations caused by 300 g rat...blanket 250 Iron 60 Broiler 130 Hair dryer 40 Vaporizer 40 Refrigerator 60 Color TV 30 Stereo 90 Coffee pot 30 Vacuum cleaner 16 Clock radio

PEP solar array definition study

NASA Technical Reports Server (NTRS)

1979-01-01

The conceptual design of a large, flexible, lightweight solar array is presented focusing on a solar array overview assessment, solar array blanket definition, structural-mechanical systems definition, and launch/reentry blanket protection features. The overview assessment includes a requirements and constraints review, the thermal environment assessment on the design selection, an evaluation of blanket integration sequence, a conceptual blanket/harness design, and a hot spot analysis considering the effects of shadowing and cell failures on overall array reliability. The solar array blanket definition includes the substrate design, hinge designs and blanket/harness flexibility assessment. The structural/mechanical systems definition includes an overall loads and deflection assessment, a frequency analysis of the deployed assembly, a components weights estimate, design of the blanket housing and tensioning mechanism. The launch/reentry blanket protection task includes assessment of solar cell/cover glass cushioning concepts during ascent and reentry flight condition.

A beamline systems model for Accelerator-Driven Transmutation Technology (ADTT) facilities

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

Todd, A.M.M.; Paulson, C.C.; Peacock, M.A.

1995-10-01

A beamline systems code, that is being developed for Accelerator-Driven Transmutation Technology (ADTT) facility trade studies, is described. The overall program is a joint Grumman, G.H. Gillespie Associates (GHGA) and Los Alamos National Laboratory effort. The GHGA Accelerator Systems Model (ASM) has been adopted as the framework on which this effort is based. Relevant accelerator and beam transport models from earlier Grumman systems codes are being adapted to this framework. Preliminary physics and engineering models for each ADTT beamline component have been constructed. Examples noted include a Bridge Coupled Drift Tube Linac (BCDTL) and the accelerator thermal system. A decisionmore » has been made to confine the ASM framework principally to beamline modeling, while detailed target/blanket, balance-of-plant and facility costing analysis will be performed externally. An interfacing external balance-of-plant and facility costing model, which will permit the performance of iterative facility trade studies, is under separate development. An ABC (Accelerator Based Conversion) example is used to highlight the present models and capabilities.« less

A beamline systems model for Accelerator-Driven Transmutation Technology (ADTT) facilities

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

Todd, Alan M. M.; Paulson, C. C.; Peacock, M. A.

1995-09-15

A beamline systems code, that is being developed for Accelerator-Driven Transmutation Technology (ADTT) facility trade studies, is described. The overall program is a joint Grumman, G. H. Gillespie Associates (GHGA) and Los Alamos National Laboratory effort. The GHGA Accelerator Systems Model (ASM) has been adopted as the framework on which this effort is based. Relevant accelerator and beam transport models from earlier Grumman systems codes are being adapted to this framework. Preliminary physics and engineering models for each ADTT beamline component have been constructed. Examples noted include a Bridge Coupled Drift Tube Linac (BCDTL) and the accelerator thermal system. Amore » decision has been made to confine the ASM framework principally to beamline modeling, while detailed target/blanket, balance-of-plant and facility costing analysis will be performed externally. An interfacing external balance-of-plant and facility costing model, which will permit the performance of iterative facility trade studies, is under separate development. An ABC (Accelerator Based Conversion) example is used to highlight the present models and capabilities.« less

KSC-04pd1783

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, Terri McCall cleans up equipment removed from the hurricane-ravaged Thermal Protection System Facility (TPSF). The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04pd1780

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, United Space Alliance worker Steve Mitchell unpacks equipment that was removed from the hurricane-ravaged Thermal Protection System Facility (TPSF). The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

Space-Spurred Metallized Materials

NASA Technical Reports Server (NTRS)

1988-01-01

Among a score of applications for a space spinoff reflective material called TXG is the emergency blanket manufactured by Metallized Products, Inc. Used by ski patrol to protect a skier shaken by a fall, the blanket retains up to 80% of user's body heat preventing post accident shock or chills. Carried by many types of emergency teams, blanket is large when unfolded, but folds into a package no larger than a deck of cards. Many other uses include, emergency blankets, all weather blanket, tanning blanket, window shields, radar reflector life raft canopies, etc.

Development of a Flammability Test Method for Aircraft Blankets

DOT National Transportation Integrated Search

1996-03-01

Flammability testing of aircraft blankets was conducted in order to develop a fire performance test method and performance criteria for blankets supplied to commercial aircraft operators. Aircraft blankets were subjected to vertical Bunsen burner tes...

Performance of silvered Teflon (trademark) thermal control blankets on spacecraft

NASA Technical Reports Server (NTRS)

Pippin, Gary; Stuckey, Wayne; Hemminger, Carol

1993-01-01

Silverized Teflon (Ag/FEP) is a widely used passive thermal control material for space applications. The material has a very low alpha/e ratio (less than 0.1) for low operating temperatures and is fabricated with various FEP thicknesses (as the Teflon thickness increases, the emittance increases). It is low outgassing and, because of its flexibility, can be applied around complex, curved shapes. Ag/FEP has achieved multiyear lifetimes under a variety of exposure conditions. This has been demonstrated by the Long Duration Exposure Facility (LDEF), Solar Max, Spacecraft Charging at High Altitudes (SCATHA), and other flight experiments. Ag/FEP material has been held in place on spacecraft by a variety of methods: mechanical clamping, direct adhesive bonding of tapes and sheets, and by Velcro(TM) tape adhesively bonded to back surfaces. On LDEF, for example, 5-mil blankets held by Velcro(TM) and clamping were used for thermal control over 3- by 4-ft areas on each of 17 trays. Adhesively bonded 2- and 5-mil sheets were used on other LDEF experiments, both for thermal control and as tape to hold other thermal control blankets in place. Performance data over extended time periods are available from a number of flights. The observed effects on optical properties, mechanical properties, and surface chemistry will be summarized in this paper. This leads to a discussion of performance life estimates and other design lessons for Ag/FEP thermal control material.

Gauge Measures Thicknesses Of Blankets

NASA Technical Reports Server (NTRS)

Hagen, George R.; Yoshino, Stanley Y.

1991-01-01

Tool makes highly repeatable measurements of thickness of penetrable blanket insulation. Includes commercial holder for replaceable knife blades, which holds needle instead of knife. Needle penetrates blanket to establish reference plane. Ballasted slider applies fixed preload to blanket. Technician reads thickness value on scale.

Toughened Thermal Blanket for MMOD Protection

NASA Technical Reports Server (NTRS)

Christiansen, Eric L.; Lear, Dana M.

2014-01-01

Thermal blankets are used extensively on spacecraft to provide passive thermal control of spacecraft hardware from thermal extremes encountered in space. Toughened thermal blankets have been developed that greatly improve protection from hypervelocity micrometeoroid and orbital debris (MMOD) impacts. These blankets can be outfitted if so desired with a reliable means to determine the location, depth and extent of MMOD impact damage by incorporating an impact sensitive piezoelectric film. Improved MMOD protection of thermal blankets was obtained by adding selective materials at various locations within the thermal blanket. As given in Figure 1, three types of materials were added to the thermal blanket to enhance its MMOD performance: (1) disrupter layers, near the outside of the blanket to improve breakup of the projectile, (2) standoff layers, in the middle of the blanket to provide an area or gap that the broken-up projectile can expand, and (3) stopper layers, near the back of the blanket where the projectile debris is captured and stopped. The best suited materials for these different layers vary. Density and thickness is important for the disrupter layer (higher densities generally result in better projectile breakup), whereas a highstrength to weight ratio is useful for the stopper layer, to improve the slowing and capture of debris particles.

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers prepare to attach an overhead crane to NASA’s MESSENGER spacecraft. The spacecraft will be moved to a work stand where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers prepare to attach an overhead crane to NASA’s MESSENGER spacecraft. The spacecraft will be moved to a work stand where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, NASA’s MESSENGER spacecraft from NASA’s Goddard Space Flight Center in Greenbelt, Md., is offloaded. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, NASA’s MESSENGER spacecraft from NASA’s Goddard Space Flight Center in Greenbelt, Md., is offloaded. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers attach an overhead crane to NASA’s MESSENGER spacecraft. The spacecraft will be moved to a work stand where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers attach an overhead crane to NASA’s MESSENGER spacecraft. The spacecraft will be moved to a work stand where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, a lift helps offload NASA’s MESSENGER spacecraft shipped from NASA’s Goddard Space Flight Center in Greenbelt, Md. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - At the Astrotech Space Operations processing facilities near KSC, a lift helps offload NASA’s MESSENGER spacecraft shipped from NASA’s Goddard Space Flight Center in Greenbelt, Md. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

Fusion nuclear science facilities and pilot plants based on the spherical tokamak

NASA Astrophysics Data System (ADS)

Menard, J. E.; Brown, T.; El-Guebaly, L.; Boyer, M.; Canik, J.; Colling, B.; Raman, R.; Wang, Z.; Zhai, Y.; Buxton, P.; Covele, B.; D'Angelo, C.; Davis, A.; Gerhardt, S.; Gryaznevich, M.; Harb, M.; Hender, T. C.; Kaye, S.; Kingham, D.; Kotschenreuther, M.; Mahajan, S.; Maingi, R.; Marriott, E.; Meier, E. T.; Mynsberge, L.; Neumeyer, C.; Ono, M.; Park, J.-K.; Sabbagh, S. A.; Soukhanovskii, V.; Valanju, P.; Woolley, R.

2016-10-01

A fusion nuclear science facility (FNSF) could play an important role in the development of fusion energy by providing the nuclear environment needed to develop fusion materials and components. The spherical torus/tokamak (ST) is a leading candidate for an FNSF due to its potentially high neutron wall loading and modular configuration. A key consideration for the choice of FNSF configuration is the range of achievable missions as a function of device size. Possible missions include: providing high neutron wall loading and fluence, demonstrating tritium self-sufficiency, and demonstrating electrical self-sufficiency. All of these missions must also be compatible with a viable divertor, first-wall, and blanket solution. ST-FNSF configurations have been developed simultaneously incorporating for the first time: (1) a blanket system capable of tritium breeding ratio TBR  ≈  1, (2) a poloidal field coil set supporting high elongation and triangularity for a range of internal inductance and normalized beta values consistent with NSTX/NSTX-U previous/planned operation, (3) a long-legged divertor analogous to the MAST-U divertor which substantially reduces projected peak divertor heat-flux and has all outboard poloidal field coils outside the vacuum chamber and superconducting to reduce power consumption, and (4) a vertical maintenance scheme in which blanket structures and the centerstack can be removed independently. Progress in these ST-FNSF missions versus configuration studies including dependence on plasma major radius R 0 for a range 1 m-2.2 m are described. In particular, it is found the threshold major radius for TBR  =  1 is {{R}0}≥slant 1.7 m, and a smaller R 0  =  1 m ST device has TBR  ≈  0.9 which is below unity but substantially reduces T consumption relative to not breeding. Calculations of neutral beam heating and current drive for non-inductive ramp-up and sustainment are described. An A  =  2, R 0  =  3 m device incorporating high-temperature superconductor toroidal field coil magnets capable of high neutron fluence and both tritium and electrical self-sufficiency is also presented following systematic aspect ratio studies.

Fusion nuclear science facilities and pilot plants based on the spherical tokamak

DOE PAGES

Menard, J. E.; Brown, T.; El-Guebaly, L.; ...

2016-08-16

Here, a fusion nuclear science facility (FNSF) could play an important role in the development of fusion energy by providing the nuclear environment needed to develop fusion materials and components. The spherical torus/tokamak (ST) is a leading candidate for an FNSF due to its potentially high neutron wall loading and modular configuration. A key consideration for the choice of FNSF configuration is the range of achievable missions as a function of device size. Possible missions include: providing high neutron wall loading and fluence, demonstrating tritium self-sufficiency, and demonstrating electrical self-sufficiency. All of these missions must also be compatible with a viable divertor, first-wall, and blanket solution. ST-FNSF configurations have been developed simultaneously incorporating for the first time: (1) a blanket system capable of tritium breeding ratio TBR ≈ 1, (2) a poloidal field coil set supporting high elongation and triangularity for a range of internal inductance and normalized beta values consistent with NSTX/NSTX-U previous/planned operation, (3) a long-legged divertor analogous to the MAST-U divertor which substantially reduces projected peak divertor heat-flux and has all outboard poloidal field coils outside the vacuum chamber and superconducting to reduce power consumption, and (4) a vertical maintenance scheme in which blanket structures and the centerstack can be removed independently. Progress in these ST-FNSF missions versus configuration studies including dependence on plasma major radius R 0 for a range 1 m–2.2 m are described. In particular, it is found the threshold major radius for TBR = 1 ismore » $${{R}_{0}}\\geqslant 1.7$$ m, and a smaller R 0 = 1 m ST device has TBR ≈ 0.9 which is below unity but substantially reduces T consumption relative to not breeding. Calculations of neutral beam heating and current drive for non-inductive ramp-up and sustainment are described. An A = 2, R = 3 m device incorporating high-temperature superconductor toroidal field coil magnets capable of high neutron fluence and both tritium and electrical self-sufficiency is also presented following systematic aspect ratio studies.« less

Thermal comfort and safety of cotton blankets warmed at 130°F and 200°F.

PubMed

Kelly, Patricia A; Cooper, Susan K; Krogh, Mary L; Morse, Elizabeth C; Crandall, Craig G; Winslow, Elizabeth H; Balluck, Julie P

2013-12-01

In 2009, the ECRI Institute recommended warming cotton blankets in cabinets set at 130°F or less. However, there is limited research to support the use of this cabinet temperature. To measure skin temperatures and thermal comfort in healthy volunteers before and after application of blankets warmed in cabinets set at 130 and 200°F, respectively, and to determine the time-dependent cooling of cotton blankets after removal from warming cabinets set at the two temperatures. Prospective, comparative, descriptive. Participants (n = 20) received one or two blankets warmed in 130 or 200°F cabinets. First, skin temperatures were measured, and thermal comfort reports were obtained at fixed timed intervals. Second, blanket temperatures (n = 10) were measured at fixed intervals after removal from the cabinets. No skin temperatures approached levels reported in the literature that cause epidermal damage. Thermal comfort reports supported using blankets from the 200°F cabinet, and blankets lost heat quickly over time. We recommend warming cotton blankets in cabinets set at 200°F or less to improve thermal comfort without compromising patient safety. Copyright © 2013 American Society of PeriAnesthesia Nurses. Published by Elsevier Inc. All rights reserved.

Three-dimensional neutronics optimization of helium-cooled blanket for multi-functional experimental fusion-fission hybrid reactor (FDS-MFX)

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

Jiang, J.; Yuan, B.; Jin, M.

2012-07-01

Three-dimensional neutronics optimization calculations were performed to analyse the parameters of Tritium Breeding Ratio (TBR) and maximum average Power Density (PDmax) in a helium-cooled multi-functional experimental fusion-fission hybrid reactor named FDS (Fusion-Driven hybrid System)-MFX (Multi-Functional experimental) blanket. Three-stage tests will be carried out successively, in which the tritium breeding blanket, uranium-fueled blanket and spent-fuel-fueled blanket will be utilized respectively. In this contribution, the most significant and main goal of the FDS-MFX blanket is to achieve the PDmax of about 100 MW/m3 with self-sustaining tritium (TBR {>=} 1.05) based on the second-stage test with uranium-fueled blanket to check and validate themore » demonstrator reactor blanket relevant technologies based on the viable fusion and fission technologies. Four different enriched uranium materials were taken into account to evaluate PDmax in subcritical blanket: (i) natural uranium, (ii) 3.2% enriched uranium, (iii) 19.75% enriched uranium, and (iv) 64.4% enriched uranium carbide. These calculations and analyses were performed using a home-developed code VisualBUS and Hybrid Evaluated Nuclear Data Library (HENDL). The results showed that the performance of the blanket loaded with 64.4% enriched uranium was the most attractive and it could be promising to effectively obtain tritium self-sufficiency (TBR-1.05) and a high maximum average power density ({approx}100 MW/m{sup 3}) when the blanket was loaded with the mass of {sup 235}U about 1 ton. (authors)« less

Weighted blankets and sleep in autistic children--a randomized controlled trial.

PubMed

Gringras, Paul; Green, Dido; Wright, Barry; Rush, Carla; Sparrowhawk, Masako; Pratt, Karen; Allgar, Victoria; Hooke, Naomi; Moore, Danielle; Zaiwalla, Zenobia; Wiggs, Luci

2014-08-01

To assess the effectiveness of a weighted-blanket intervention in treating severe sleep problems in children with autism spectrum disorder (ASD). This phase III trial was a randomized, placebo-controlled crossover design. Participants were aged between 5 years and 16 years 10 months, with a confirmed ASD diagnosis and severe sleep problems, refractory to community-based interventions. The interventions were either a commercially available weighted blanket or otherwise identical usual weight blanket (control), introduced at bedtime; each was used for a 2-week period before crossover to the other blanket. Primary outcome was total sleep time (TST) recorded by actigraphy over each 2-week period. Secondary outcomes included actigraphically recorded sleep-onset latency, sleep efficiency, assessments of child behavior, family functioning, and adverse events. Sleep was also measured by using parent-report diaries. Seventy-three children were randomized and analysis conducted on 67 children who completed the study. Using objective measures, the weighted blanket, compared with the control blanket, did not increase TST as measured by actigraphy and adjusted for baseline TST. There were no group differences in any other objective or subjective measure of sleep, including behavioral outcomes. On subjective preference measures, parents and children favored the weighted blanket. The use of a weighted blanket did not help children with ASD sleep for a longer period of time, fall asleep significantly faster, or wake less often. However, the weighted blanket was favored by children and parents, and blankets were well tolerated over this period. Copyright © 2014 by the American Academy of Pediatrics.

Follow-up on the effects of the space environment on UHCRE thermal blankets

NASA Technical Reports Server (NTRS)

Levadou, Francois; Vaneesbeek, Marc

1993-01-01

An overview of the effects of the space environment on the thermal blanket of the UHCRE experiment is presented with an emphasis on atomic oxygen (AO) erosion. A more accurate value for FEP Teflon reaction efficiency is given and corresponds, at normal incidence, to 3.24 10(exp -25) cu cm/atomic, therefore, the FEP Teflon erosion corresponding to the Long Duration Exposure Facility (LDEF) total mission is 29.5 microns. A power 1.44 of the cosine of the incident angle of the oxygen atoms is found. It is shown that this value is not far from the power found using Fergusson's relationship between efficiency and energy of the O-atoms. An hypothesis concerning the effect of oxygen ions (O(+)) is also presented. The presence of oxygen ions may explain the different results obtained from different flights and from laboratory tests. Finally an XPS analysis of Chemglaze Z306(tm) black paint demonstrates the presence of silicone in the paint which may explain part of the contamination found on LDEF.

Fusion technologies for Laser Inertial Fusion Energy (LIFE)

NASA Astrophysics Data System (ADS)

Kramer, K. J.; Latkowski, J. F.; Abbott, R. P.; Anklam, T. P.; Dunne, A. M.; El-Dasher, B. S.; Flowers, D. L.; Fluss, M. J.; Lafuente, A.; Loosmore, G. A.; Morris, K. R.; Moses, E.; Reyes, S.

2013-11-01

The Laser Inertial Fusion-based Energy (LIFE) engine design builds upon on going progress at the National Ignition Facility (NIF) and offers a near-term pathway to commercial fusion. Fusion technologies that are critical to success are reflected in the design of the first wall, blanket and tritium separation subsystems. The present work describes the LIFE engine-related components and technologies. LIFE utilizes a thermally robust indirect-drive target and a chamber fill gas. Coolant selection and a large chamber solid-angle coverage provide ample tritium breeding margin and high blanket gain. Target material selection eliminates the need for aggressive chamber clearing, while enabling recycling. Demonstrated tritium separation and storage technologies limit the site tritium inventory to attractive levels. These key technologies, along with the maintenance and advanced materials qualification program have been integrated into the LIFE delivery plan. This describes the development of components and subsystems, through prototyping and integration into a First Of A Kind power plant. This work performed under the auspices of the U.S. Department of Energy by Lawrence Livermore National Laboratory under Contract DE-AC52-07NA27344.

STS-97 P6 truss moves to a payload transport canister

NASA Technical Reports Server (NTRS)

2000-01-01

As it travels across the Space Station Processing Facility, the P6 integrated truss segment passes over the two Italian-built Multi-Purpose Logistics Modules, Leonardo (right) and Raffaello (behind Leonardo). The P6 is being moved to a payload transport canister for transfer to Launch Pad 39B. There it will be placed in Endeavour'''s payload bay for launch on mission STS-97. The P6 comprises Solar Array Wing-3 and the Integrated Electronic Assembly, to be installed on the Space Station. The Station'''s electrical power system will use eight photovoltaic solar arrays, each 112 feet long by 39 feet wide, to convert sunlight to electricity. The solar arrays are mounted on a '''blanket''' that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station. Launch is scheduled Nov. 30 at 10:06 p.m. EST.

Thin Thermal-Insulation Blankets for Very High Temperatures

NASA Technical Reports Server (NTRS)

Choi, Michael K.

2003-01-01

Thermal-insulation blankets of a proposed type would be exceptionally thin and would endure temperatures up to 2,100 C. These blankets were originally intended to protect components of the NASA Solar Probe spacecraft against radiant heating at its planned closest approach to the Sun (a distance of 4 solar radii). These blankets could also be used on Earth to provide thermal protection in special applications (especially in vacuum chambers) for which conventional thermal-insulation blankets would be too thick or would not perform adequately.

KSC-04PD-1785

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the RLV hangar at KSC, Steve Harrington talks to workers about the equipment removed from the hurricane-ravaged Thermal Protection System Facility (TPSF) now being stored in the hangar. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04PD-1782

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the RLV hangar at KSC, United Space Alliance workers Frank Rhodes and Lynn Rosenbauer look at wrapped material removed from the hurricane-ravaged Thermal Protection System Facility (TPSF). The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-08pd2291

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment (MULE) carrier arrives at the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-04pd1788

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, Kevin Harrington, manager of Softgoods Production, talks to workers about the equipment removed from the hurricane-ravaged Thermal Protection System Facility (TPSF) now being stored in the hangar. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04pd1792

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, United Space Alliance workers set up shelves for equipment removed from the hurricane-ravaged Thermal Protection System Facility (TPSF) and now being stored in the hangar. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04pd1786

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, Steve Harrington talks to workers about the equipment removed from the hurricane-ravaged Thermal Protection System Facility (TPSF) now being stored in the hangar. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04pd1785

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, Steve Harrington talks to workers about the equipment removed from the hurricane-ravaged Thermal Protection System Facility (TPSF) now being stored in the hangar. The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04pd1782

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, United Space Alliance workers Frank Rhodes and Lynn Rosenbauer look at wrapped material removed from the hurricane-ravaged Thermal Protection System Facility (TPSF). The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04pd1784

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, United Space Alliance workers Matt Carter (left) and Mike Sherman set up racks to hold equipment removed from the hurricane-ravaged Thermal Protection System Facility (TPSF). The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04pd1781

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - In the RLV hangar at KSC, United Space Alliance workers Beth Smith (left) and Theresa Haygood unwrap equipment removed from the hurricane-ravaged Thermal Protection System Facility (TPSF). The facility, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-2009-2472

NASA Image and Video Library

2009-03-19

CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla., the GOES-O satellite is rotated on a stand toward a vertical position after blanket inspection. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. The GOES-O satellite is targeted to launch April 28 onboard a United Launch Alliance Delta IV expendable launch vehicle. Photo credit: NASA/Jim Grossmann

KSC-2009-2470

NASA Image and Video Library

2009-03-19

CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla., the GOES-O satellite is rotated on a stand for blanket inspection. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. The GOES-O satellite is targeted to launch April 28 onboard a United Launch Alliance Delta IV expendable launch vehicle. Photo credit: NASA/Jim Grossmann

KSC-2009-2469

NASA Image and Video Library

2009-03-19

CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla., the GOES-O satellite is rotated on a stand for blanket inspection. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. The GOES-O satellite is targeted to launch April 28 onboard a United Launch Alliance Delta IV expendable launch vehicle. Photo credit: NASA/Jim Grossmann

KSC-2009-2468

NASA Image and Video Library

2009-03-19

CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla., the GOES-O satellite is rotated on a stand for blanket inspection. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. The GOES-O satellite is targeted to launch April 28 onboard a United Launch Alliance Delta IV expendable launch vehicle. Photo credit: NASA/Jim Grossmann

KSC-2009-2473

NASA Image and Video Library

2009-03-19

CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla., the GOES-O satellite has been rotated on its stand to a vertical position after blanket inspection. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. The GOES-O satellite is targeted to launch April 28 onboard a United Launch Alliance Delta IV expendable launch vehicle. Photo credit: NASA/Jim Grossmann

KSC-2009-2471

NASA Image and Video Library

2009-03-19

CAPE CANAVERAL, Fla. – In the Astrotech payload processing facility in Titusville, Fla., the GOES-O satellite is rotated on a stand for blanket inspection. The latest Geostationary Operational Environmental Satellite, GOES-O was developed by NASA for the National Oceanic and Atmospheric Administration, or NOAA. Once in orbit, GOES-O will be designated GOES-14, and NASA will provide on-orbit checkout and then transfer operational responsibility to NOAA. The GOES-O satellite is targeted to launch April 28 onboard a United Launch Alliance Delta IV expendable launch vehicle. Photo credit: NASA/Jim Grossmann

KSC-04pd0703

NASA Image and Video Library

2004-04-05

KENNEDY SPACE CENTER, FLA. -- United Space Alliance (USA) technician Mike Williams (left) checks a portion of the thermal blanket insulation to be installed in Discovery’s nose cap. Looking from underneath is R. Justin Hopmann, with USA. In the background is Pearl Richardson, also with USA, next to the work stand holding the nose cap, which is under a protective cover. The work is being done in a low bay area outside the Orbiter Processing Facility. Discovery is the orbiter named as the vehicle for Return to Flight with mission STS-114.

Comprehensive Experiments on Subcritical Assemblies of Cascade Reactor Systems

NASA Astrophysics Data System (ADS)

Zavyalov, N. V.; Il'kaev, R. I.; Kolesov, V. F.; Ivanin, I. A.; Zhitnik, A. K.; Kuvshinov, M. I.; Nefedov, Yu. Ya.; Punin, V. T.; Tel'nov, A. V.; Khoruzhi, V. Kh.

2017-12-01

Cascade reactors attract particular attention because of their capability of improving the parameters of pulsed reactors and achieving the feasibility of electronuclear facilities. The paper presents the results of three series of experiments on uranium-neptunium cascade assemblies at the Institute of Nuclear and Radiation Physics of the All-Russian Research Institute of Experimental Physics conducted in 2003-2004. The experiments confirmed theoretical conclusions on positive properties of cascade blankets and effectiveness of using neptunium-237 as a means of creating a one-sided connection between the sections.

KSC-04pd0600

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers secure NASA’s MESSENGER spacecraft on a test stand. Once in place, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

KSC-04pd0601

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers secure NASA’s MESSENGER spacecraft on a test stand. Once in place, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

KSC-04pd0602

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers secure NASA’s MESSENGER spacecraft on a test stand. Once in place, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

OA-7 Nano-rack Installation

NASA Image and Video Library

2017-02-27

Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, technicians install thermal blankets around the area where several Nanoracks will be installed on the exterior of the Orbital ATK Cygnus pressurized cargo module. The Orbital ATK CRS-7 commercial resupply services mission to the International Space Station is scheduled to launch atop a United Launch Alliance Atlas V rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station no earlier than March 21, 2017. Cygnus will deliver 7,600 pounds of supplies, equipment and scientific research materials to the space station.

OA-7 Nano-rack Installation

NASA Image and Video Library

2017-02-27

Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, technicians prepare thermal blankets for several Nanoracks that will be installed on the exterior of the Orbital ATK Cygnus pressurized cargo module. The Orbital ATK CRS-7 commercial resupply services mission to the International Space Station is scheduled to launch atop a United Launch Alliance Atlas V rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station no earlier than March 21, 2017. Cygnus will deliver 7,600 pounds of supplies, equipment and scientific research materials to the space station.

KSC-04PD-1680

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, workers help guide the nose cap (right) toward the orbiter Atlantis for installation. The nose cap was removed from the vehicle in May and sent back to the vendor for thorough Non- Destructive Engineering evaluation and recoating. Thermography was also performed to check for internal flaws. This procedure uses high intensity light to heat areas that are immediately scanned with an infrared camera. White Thermal Protection System blankets were reinstalled on the nose cap before installation. Processing continues on Atlantis for its future mission to the International Space Station.

KSC-04PD-1681

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, workers help install the nose cap (right) onto the orbiter Atlantis. The nose cap was removed from the vehicle in May and sent back to the vendor for thorough Non-Destructive Engineering evaluation and recoating. Thermography was also performed to check for internal flaws. This procedure uses high intensity light to heat areas that are immediately scanned with an infrared camera. White Thermal Protection System blankets were reinstalled on the nose cap before installation. Processing continues on Atlantis for its future mission to the International Space Station.

Updated neutronics analyses of a water cooled ceramic breeder blanket for the CFETR

NASA Astrophysics Data System (ADS)

Xiaokang, ZHANG; Songlin, LIU; Xia, LI; Qingjun, ZHU; Jia, LI

2017-11-01

The water cooled ceramic breeder (WCCB) blanket employing pressurized water as a coolant is one of the breeding blanket candidates for the China Fusion Engineering Test Reactor (CFETR). Some updating of neutronics analyses was needed, because there were changes in the neutronics performance of the blanket as several significant modifications and improvements have been adopted for the WCCB blanket, including the optimization of radial build-up and customized structure for each blanket module. A 22.5 degree toroidal symmetrical torus sector 3D neutronics model containing the updated design of the WCCB blanket modules was developed for the neutronics analyses. The tritium breeding capability, nuclear heating power, radiation damage, and decay heat were calculated by the MCNP and FISPACT code. The results show that the packing factor and 6Li enrichment of the breeder should both be no less than 0.8 to ensure tritium self-sufficiency. The nuclear heating power of the blanket under 200 MW fusion power reaches 201.23 MW. The displacement per atom per full power year (FPY) of the plasma-facing component and first wall reach 0.90 and 2.60, respectively. The peak H production rate reaches 150.79 appm/FPY and the peak He production reaches 29.09 appm/FPY in blanket module #3. The total decay heat of the blanket modules is 2.64 MW at 1 s after shutdown and the average decay heat density can reach 11.09 kW m-3 at that time. The decay heat density of the blanket modules slowly decreases to lower than 10 W m-3 in more than ten years.

Management of horses with focus on blanketing and clipping practices reported by members of the Swedish and Norwegian equestrian community.

PubMed

Hartmann, E; Bøe, K E; Jørgensen, G H M; Mejdell, C M; Dahlborn, K

2017-03-01

Limited information is available on the extent to which blankets are used on horses and the owners' reasoning behind clipping the horse's coat. Research on the effects of those practices on horse welfare is scarce but results indicate that blanketing and clipping may not be necessary from the horse's perspective and can interfere with the horse's thermoregulatory capacities. Therefore, this survey collected robust, quantitative data on the housing routines and management of horses with focus on blanketing and clipping practices as reported by members of the Swedish and Norwegian equestrian community. Horse owners were approached via an online survey, which was distributed to equestrian organizations and social media. Data from 4,122 Swedish and 2,075 Norwegian respondents were collected, of which 91 and 84% of respondents, respectively, reported using blankets on horses during turnout. Almost all respondents owning warmblood riding horses used blankets outdoors (97% in Sweden and 96% in Norway) whereas owners with Icelandic horses and coldblood riding horses used blankets significantly less ( < 0.05). Blankets were mainly used during rainy, cold, or windy weather conditions and in ambient temperatures of 10°C and below. The horse's coat was clipped by 67% of respondents in Sweden and 35% of Norwegian respondents whereby owners with warmblood horses and horses primarily used for dressage and competition reported clipping the coat most frequently. In contrast to scientific results indicating that recovery time after exercise increases with blankets and that clipped horses have a greater heat loss capacity, only around 50% of respondents agreed to these statements. This indicates that evidence-based information on all aspects of blanketing and clipping has not yet been widely distributed in practice. More research is encouraged, specifically looking at the effect of blankets on sweaty horses being turned out after intense physical exercise and the effect of blankets on social interactions such as mutual grooming. Future efforts should be tailored to disseminate knowledge more efficiently, which can ultimately stimulate thoughtful decision-making by horse owners concerning the use of blankets and clipping the horse's coat.

KSC-04pd1851

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - Looking at damage inside the hurricane-ravaged Thermal Protection System Facility are KSC Director of Spaceport Services Scott Kerr (left) and NASA Associate Administrator of Space Operations Mission Directorate William Readdy (right). The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof during Hurricane Frances, which blew across Central Florida Sept. 4-5. Readdy and NASA Administrator Sean O’Keefe are visiting KSC to survey the damage sustained by KSC facilities from the hurricane. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters - Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

75 FR 38459 - Certain Woven Electric Blankets From the People's Republic of China: Final Determination of Sales...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-07-02

... Industries (``Perfect Fit''), a U.S. importer of knitted electric blankets, submitted comments on the scope... investigation to include the following two statements: (1) ``knitted electric blankets in any form, whether... acknowledged that knitted electric blankets and electric mattress pads are not within the scope of the U.S...

Ceramic insulation/multifoil composite for thermal protection of reentry spacecraft

NASA Technical Reports Server (NTRS)

Pitts, W. C.; Kourtides, D. A.

1989-01-01

A new type of insulation blanket called Composite Flexible Blanket Insulation is proposed for thermal protection of advanced spacecraft in regions where the maximum temperature is not excessive. The blanket is a composite of two proven insulation materials: ceramic insulation blankets from Space Shuttle technology and multilayer insulation blankets from spacecraft thermal control technology. A potential heatshield weight saving of up to 500 g/sq m is predicted. The concept is described; proof of concept experimental data are presented; and a spaceflight experiment to demonstrate its actual performance is discussed.

Packed fluidized bed blanket for fusion reactor

DOEpatents

Chi, John W. H.

1984-01-01

A packed fluidized bed blanket for a fusion reactor providing for efficient radiation absorption for energy recovery, efficient neutron absorption for nuclear transformations, ease of blanket removal, processing and replacement, and on-line fueling/refueling. The blanket of the reactor contains a bed of stationary particles during reactor operation, cooled by a radial flow of coolant. During fueling/refueling, an axial flow is introduced into the bed in stages at various axial locations to fluidize the bed. When desired, the fluidization flow can be used to remove particles from the blanket.

A New Fire Hazard for MR Imaging Systems: Blankets-Case Report.

PubMed

Bertrand, Anne; Brunel, Sandrine; Habert, Marie-Odile; Soret, Marine; Jaffre, Simone; Capeau, Nicolas; Bourseul, Laetitia; Dufour-Claude, Isabelle; Kas, Aurélie; Dormont, Didier

2018-02-01

In this report, a case of fire in a positron emission tomography (PET)/magnetic resonance (MR) imaging system due to blanket combustion is discussed. Manufacturing companies routinely use copper fibers for blanket fabrication, and these fibers may remain within the blanket hem. By folding a blanket with these copper fibers within an MR imaging system, one can create an electrical current loop with a major risk of local excessive heating, burn injury, and fire. This hazard applies to all MR imaging systems. Hybrid PET/MR imaging systems may be particularly vulnerable to this situation, because blankets are commonly used for fluorodeoxyglucose PET to maintain a normal body temperature and to avoid fluorodeoxyglucose uptake in brown adipose tissue. © RSNA, 2017.

KSC-04pd1842

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - NASA Administrator Sean O’Keefe looks at equipment moved from the Thermal Protection System Facility to the RLV Hangar. AT right is Martin Wilson, manager of TPS operations for United Space Alliance. O’Keefe and NASA Associate Administrator of Space Operations Mission Directorate William Readdy are visiting KSC to survey the damage sustained by KSC facilities from Hurricane Frances. The Thermal Protection System Facility (TPSF), which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof in the storm, which blew across Central Florida Sept. 4-5. Undamaged equipment was removed from the TPSF and stored in the hangar. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters -- Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

KSC-04pd1843

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - - NASA Administrator Sean O’Keefe (right) looks at equipment moved from the Thermal Protection System Facility to the RLV Hangar. At left are United Space Alliance technicians Shelly Kipp and Eric Moss. O’Keefe and NASA Associate Administrator of Space Operations Mission Directorate William Readdy are visiting KSC to survey the damage sustained by KSC facilities from Hurricane Frances. The Thermal Protection System Facility (TPSF), which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof in the storm, which blew across Central Florida Sept. 4-5. Undamaged equipment was removed from the TPSF and stored in the hangar. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters - Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

Postirradiation thermocyclic loading of ferritic-martensitic structural materials

NASA Astrophysics Data System (ADS)

Belyaeva, L.; Orychtchenko, A.; Petersen, C.; Rybin, V.

Thermonuclear fusion reactors of the Tokamak-type will be unique power engineering plants to operate in thermocyclic mode only. Ferritic-martensitic stainless steels are prime candidate structural materials for test blankets of the ITER fusion reactor. Beyond the radiation damage, thermomechanical cyclic loading is considered as the most detrimental lifetime limiting phenomenon for the above structure. With a Russian and a German facility for thermal fatigue testing of neutron irradiated materials a cooperation has been undertaken. Ampule devices to irradiate specimens for postirradiation thermal fatigue tests have been developed by the Russian partner. The irradiation of these ampule devices loaded with specimens of ferritic-martensitic steels, like the European MANET-II, the Russian 05K12N2M and the Japanese Low Activation Material F82H-mod, in a WWR-M-type reactor just started. A description of the irradiation facility, the qualification of the ampule device and the modification of the German thermal fatigue facility will be presented.

An overview of research activities on materials for nuclear applications at the INL Safety, Tritium and Applied Research facility

NASA Astrophysics Data System (ADS)

Calderoni, P.; Sharpe, J.; Shimada, M.; Denny, B.; Pawelko, B.; Schuetz, S.; Longhurst, G.; Hatano, Y.; Hara, M.; Oya, Y.; Otsuka, T.; Katayama, K.; Konishi, S.; Noborio, K.; Yamamoto, Y.

2011-10-01

The Safety, Tritium and Applied Research facility at the Idaho National Laboratory is a US Department of Energy National User Facility engaged in various aspects of materials research for nuclear applications related to fusion and advanced fission systems. Research activities are mainly focused on the interaction of tritium with materials, in particular plasma facing components, liquid breeders, high temperature coolants, fuel cladding, cooling and blanket structures and heat exchangers. Other activities include validation and verification experiments in support of the Fusion Safety Program, such as beryllium dust reactivity and dust transport in vacuum vessels, and support of Advanced Test Reactor irradiation experiments. This paper presents an overview of the programs engaged in the activities, which include the US-Japan TITAN collaboration, the US ITER program, the Next Generation Power Plant program and the tritium production program, and a presentation of ongoing experiments as well as a summary of recent results with emphasis on fusion relevant materials.

Self-cooled liquid-metal blanket concept

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

Malang, S.; Arheidt, K.; Barleon, L.

1988-11-01

A blanket concept for the Next European Torus (NET) where 83Pb-17Li serves both as breeder material and as coolant is described. The concept is based on the use of novel flow channel inserts for a decisive reduction of the magnetohydrodynamic (MHD) pressure drop and employs beryllium as neutron multiplier in order to avoid the need for breeding blankets at the inboard side of the torus. This study includes the design, neutronics, thermal hydraulics, stresses, MHDs, corrosion, tritium recovery, and safety of a self-cooled liquid-metal blanket. The results of the investigations indicate that the self-cooled blanket is an attractive alternative tomore » other driver blanket concepts for NET and that it can be extrapolated to the conditions of a DEMO reactor.« less

Comparison of forced-air warming systems with lower body blankets using a copper manikin of the human body.

PubMed

Bräuer, A; English, M J M; Lorenz, N; Steinmetz, N; Perl, T; Braun, U; Weyland, W

2003-01-01

Forced-air warming has gained high acceptance as a measure for the prevention of intraoperative hypothermia. However, data on heat transfer with lower body blankets are not yet available. This study was conducted to determine the heat transfer efficacy of six complete lower body warming systems. Heat transfer of forced-air warmers can be described as follows:[1]Qdot;=h.DeltaT.A where Qdot; = heat transfer [W], h = heat exchange coefficient [W m-2 degrees C-1], DeltaT = temperature gradient between blanket and surface [ degrees C], A = covered area [m2]. We tested the following forced-air warmers in a previously validated copper manikin of the human body: (1) Bair Hugger and lower body blanket (Augustine Medical Inc., Eden Prairie, MN); (2) Thermacare and lower body blanket (Gaymar Industries, Orchard Park, NY); (3) WarmAir and lower body blanket (Cincinnati Sub-Zero Products, Cincinnati, OH); (4) Warm-Gard(R) and lower body blanket (Luis Gibeck AB, Upplands Väsby, Sweden); (5) Warm-Gard and reusable lower body blanket (Luis Gibeck AB); and (6) WarmTouch and lower body blanket (Mallinckrodt Medical Inc., St. Luis, MO). Heat flux and surface temperature were measured with 16 calibrated heat flux transducers. Blanket temperature was measured using 16 thermocouples. DeltaT was varied between -10 and +10 degrees C and h was determined by a linear regression analysis as the slope of DeltaT vs. heat flux. Mean DeltaT was determined for surface temperatures between 36 and 38 degrees C, because similar mean skin temperatures have been found in volunteers. The area covered by the blankets was estimated to be 0.54 m2. Heat transfer from the blanket to the manikin was different for surface temperatures between 36 degrees C and 38 degrees C. At a surface temperature of 36 degrees C the heat transfer was higher (between 13.4 W to 18.3 W) than at surface temperatures of 38 degrees C (8-11.5 W). The highest heat transfer was delivered by the Thermacare system (8.3-18.3 W), the lowest heat transfer was delivered by the Warm-Gard system with the single use blanket (8-13.4 W). The heat exchange coefficient varied between 12.5 W m-2 degrees C-1 and 30.8 W m-2 degrees C-1, mean DeltaT varied between 1.04 degrees C and 2.48 degrees C for surface temperatures of 36 degrees C and between 0.50 degrees C and 1.63 degrees C for surface temperatures of 38 degrees C. No relevant differences in heat transfer of lower body blankets were found between the different forced-air warming systems tested. Heat transfer was lower than heat transfer by upper body blankets tested in a previous study. However, forced-air warming systems with lower body blankets are still more effective than forced-air warming systems with upper body blankets in the prevention of perioperative hypothermia, because they cover a larger area of the body surface.

NUCLEAR REACTOR

DOEpatents

Sherman, J.; Sharbaugh, J.E.; Fauth, W.L. Jr.; Palladino, N.J.; DeHuff, P.G.

1962-10-23

A nuclear reactor incorporating seed and blanket assemblies is designed. Means are provided for obtaining samples of the coolant from the blanket assemblies and for varying the flow of coolant through the blanket assemblies. (AEC)

KENNEDY SPACE CENTER, FLA. - Doors are open on the air-conditioned transportation van that carried NASA’s MESSENGER spacecraft from NASA’s Goddard Space Flight Center in Greenbelt, Md., to the Astrotech Space Operations processing facilities near KSC. After offloading, MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - Doors are open on the air-conditioned transportation van that carried NASA’s MESSENGER spacecraft from NASA’s Goddard Space Flight Center in Greenbelt, Md., to the Astrotech Space Operations processing facilities near KSC. After offloading, MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

Mechanical design

NASA Technical Reports Server (NTRS)

1976-01-01

Design concepts for a 1000 mw thermal stationary power plant employing the UF6 fueled gas core breeder reactor are examined. Three design combinations-gaseous UF6 core with a solid matrix blanket, gaseous UF6 core with a liquid blanket, and gaseous UF6 core with a circulating blanket were considered. Results show the gaseous UF6 core with a circulating blanket was best suited to the power plant concept.

Storing and Deploying Solar Panels

NASA Technical Reports Server (NTRS)

Browning, D. L.; Stocker, H. M.; Kleidon, E. H.

1982-01-01

Like upward-drawn window shades, solar blankets are unfurled to length of 89m, almost filling opening in 95.59-meter-square frame. When frame is completely assembled, solar blankets are pulled from canisters, one by one by electric motor. A Thin cushion sheet is rolled up with each blanket to cushion solar cells. Sheet is taken up on roller as blanket is unfurled. Unrolling proceeds automatically.

Phase 3 experiments of the JAERI/USDOE collaborative program on fusion blanket neutronics. Volume 1: Experiment

NASA Astrophysics Data System (ADS)

Oyama, Yukio; Konno, Chikara; Ikeda, Yujiro; Maekawa, Fujio; Kosako, Kazuaki; Nakamura, Tomoo; Maekawa, Hiroshi; Youssef, Mahmoud Z.; Kumar, Anil; Abdou, Mohamed A.

1994-02-01

A pseudo-line source has been realized by using an accelerator based D-T point neutron source. The pseudo-line source is obtained by time averaging of continuously moving point source or by superposition of finely distributed point sources. The line source is utilized for fusion blanket neutronics experiments with an annular geometry so as to simulate a part of a tokamak reactor. The source neutron characteristics were measured for two operational modes for the line source, continuous and step-wide modes, with the activation foil and the NE213 detectors, respectively. In order to give a source condition for a successive calculational analysis on the annular blanket experiment, the neutron source characteristics was calculated by a Monte Carlo code. The reliability of the Monte Carlo calculation was confirmed by comparison with the measured source characteristics. The shape of the annular blanket system was a rectangular with an inner cavity. The annular blanket was consist of 15 mm-thick first wall (SS304) and 406 mm-thick breeder zone with Li2O at inside and Li2CO3 at outside. The line source was produced at the center of the inner cavity by moving the annular blanket system in the span of 2 m. Three annular blanket configurations were examined; the reference blanket, the blanket covered with 25 mm thick graphite armor and the armor-blanket with a large opening. The neutronics parameters of tritium production rate, neutron spectrum and activation reaction rate were measured with specially developed techniques such as multi-detector data acquisition system, spectrum weighting function method and ramp controlled high voltage system. The present experiment provides unique data for a higher step of benchmark to test a reliability of neutronics design calculation for a realistic tokamak reactor.

Analysis and optimization of minor actinides transmutation blankets with regards to neutron and gamma sources

NASA Astrophysics Data System (ADS)

Kooymana, Timothée; Buiron, Laurent; Rimpault, Gérald

2017-09-01

Heterogeneous loading of minor actinides in radial blankets is a potential solution to implement minor actinides transmutation in fast reactors. However, to compensate for the lower flux level experienced by the blankets, the fraction of minor actinides to be loaded in the blankets must be increased to maintain acceptable performances. This severely increases the decay heat and neutron source of the blanket assemblies, both before and after irradiation, by more than an order of magnitude in the case of neutron source for instance. We propose here to implement an optimization methodology of the blankets design with regards to various parameters such as the local spectrum or the mass to be loaded, with the objective of minimizing the final neutron source of the spent assembly while maximizing the transmutation performances of the blankets. In a first stage, an analysis of the various contributors to long and short term neutron and gamma source is carried out while in a second stage, relevant estimators are designed for use in the effective optimization process, which is done in the last step. A comparison with core calculations is finally done for completeness and validation purposes. It is found that the use of a moderated spectrum in the blankets can be beneficial in terms of final neutron and gamma source without impacting minor actinides transmutation performances compared to more energetic spectrum that could be achieved using metallic fuel for instance. It is also confirmed that, if possible, the use of hydrides as moderating material in the blankets is a promising option to limit the total minor actinides inventory in the fuel cycle. If not, it appears that focus should be put upon an increased residence time for the blankets rather than an increase in the acceptable neutron source for handling and reprocessing.

KSC-08pd2315

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, technicians remove the protective cover from the Multi-Use Lightweight Equipment, or MULE, carrier. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2297

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, the cover of the shipping container is lifted to reveal the Multi-Use Lightweight Equipment (MULE) carrier inside. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2316

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, a technician removes the protective cover from the Multi-Use Lightweight Equipment, or MULE, carrier. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2312

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Multi-Use Lightweight Equipment, or MULE, carrier toward a stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2314

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, a technician begins removing the protective cover from the Multi-Use Lightweight Equipment, or MULE, carrier. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2298

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, arcane moves the cover of the shipping container away from its cargo, the Multi-Use Lightweight Equipment (MULE) carrier. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2289

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – At the Canister Rotation Facility at NASA's Kennedy Space Center, the shipping container with the Multi-Use Lightweight Equipment (MULE) carrier inside is pressure cleaned after its arrival. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2306

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment, or MULE, carrier is waiting to be moved onto another stand in the high bay in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Jack Pfaller

KSC-08pd2313

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, the Multi-Use Lightweight Equipment, or MULE, carrier rests on a stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2296

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, the cover of the shipping container is lifted to reveal the Multi-Use Lightweight Equipment (MULE) carrier inside. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2305

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment, or MULE, carrier is moved into the high bay in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Jack Pfaller

KSC-08pd2311

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane lowers the Multi-Use Lightweight Equipment, or MULE, carrier toward a stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2317

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment, or MULE, carrier is revealed after its protective cover was removed in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2300

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, the Multi-Use Lightweight Equipment (MULE) carrier awaits a move into the clean-room high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2292

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – A transporter moves the shipping container with the Multi-Use Lightweight Equipment (MULE) carrier toward the open doors of the airlock in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2304

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment, or MULE, carrier is being moved into the high bay in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Jack Pfaller

KSC-08pd2293

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – The shipping container with the Multi-Use Lightweight Equipment (MULE) carrier inside is moved into the airlock in the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

48 CFR 313.303 - Blanket purchase agreements.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 48 Federal Acquisition Regulations System 4 2010-10-01 2010-10-01 false Blanket purchase agreements. 313.303 Section 313.303 Federal Acquisition Regulations System HEALTH AND HUMAN SERVICES....303 Blanket purchase agreements. ...

Comparison of forced-air warming systems with upper body blankets using a copper manikin of the human body.

PubMed

Bräuer, A; English, M J M; Steinmetz, N; Lorenz, N; Perl, T; Braun, U; Weyland, W

2002-09-01

Forced-air warming with upper body blankets has gained high acceptance as a measure for the prevention of intraoperative hypothermia. However, data on heat transfer with upper body blankets are not yet available. This study was conducted to determine the heat transfer efficacy of eight complete upper body warming systems and to gain more insight into the principles of forced-air warming. Heat transfer of forced-air warmers can be described as follows: Qdot;=h. DeltaT. A, where Qdot;= heat flux [W], h=heat exchange coefficient [W m-2 degrees C-1], DeltaT=temperature gradient between the blanket and surface [ degrees C], and A=covered area [m2]. We tested eight different forced-air warming systems: (1) Bair Hugger and upper body blanket (Augustine Medical Inc. Eden Prairie, MN); (2) Thermacare and upper body blanket (Gaymar Industries, Orchard Park, NY); (3) Thermacare (Gaymar Industries) with reusable Optisan upper body blanket (Willy Rüsch AG, Kernen, Germany); (4) WarmAir and upper body blanket (Cincinnati Sub-Zero Products, Cincinnati, OH); (5) Warm-Gard and single use upper body blanket (Luis Gibeck AB, Upplands Väsby, Sweden); (6) Warm-Gard and reusable upper body blanket (Luis Gibeck AB); (7) WarmTouch and CareDrape upper body blanket (Mallinckrodt Medical Inc., St. Luis, MO); and (8) WarmTouch and reusable MultiCover trade mark upper body blanket (Mallinckrodt Medical Inc.) on a previously validated copper manikin of the human body. Heat flux and surface temperature were measured with 11 calibrated heat flux transducers. Blanket temperature was measured using 11 thermocouples. The temperature gradient between the blanket and surface (DeltaT) was varied between -8 and +8 degrees C, and h was determined by linear regression analysis as the slope of DeltaT vs. heat flux. Mean DeltaT was determined for surface temperatures between 36 and 38 degrees C, as similar mean skin surface temperatures have been found in volunteers. The covered area was estimated to be 0.35 m2. Total heat flow from the blanket to the manikin was different for surface temperatures between 36 and 38 degrees C. At a surface temperature of 36 degrees C the heat flows were higher (4-26.6 W) than at surface temperatures of 38 degrees C (2.6-18.1 W). The highest total heat flow was delivered by the WarmTouch trade mark system with the CareDrape trade mark upper body blanket (18.1-26.6 W). The lowest total heat flow was delivered by the Warm-Gard system with the single use upper body blanket (2.6-4 W). The heat exchange coefficient varied between 15.1 and 36.2 W m-2 degrees C-1, and mean DeltaT varied between 0.5 and 3.3 degrees C. We found total heat flows of 2.6-26.6 W by forced-air warming systems with upper body blankets. However, the changes in heat balance by forced-air warming systems with upper body blankets are larger, as these systems are not only transferring heat to the body but are also reducing heat losses from the covered area to zero. Converting heat losses of approximately 37.8 W to heat gain, results in a 40.4-64.4 W change in heat balance. The differences between the systems result from different heat exchange coefficients and different mean temperature gradients. However, the combination of a high heat exchange coefficient with a high mean temperature gradient is rare. This fact offers some possibility to improve these systems.

Spacecraft thermal blanket cleaning: Vacuum bake of gaseous flow purging

NASA Technical Reports Server (NTRS)

Scialdone, John J.

1990-01-01

The mass losses and the outgassing rates per unit area of three thermal blankets consisting of various combinations of Mylar and Kapton, with interposed Dacron nets, were measured with a microbalance using two methods. The blankets at 25 deg C were either outgassed in vacuum for 20 hours, or were purged with a dry nitrogen flow of 3 cu. ft. per hour at 25 deg C for 20 hours. The two methods were compared for their effectiveness in cleaning the blankets for their use in space applications. The measurements were carried out using blanket strips and rolled-up blanket samples fitting the microbalance cylindrical plenum. Also, temperature scanning tests were carried out to indicate the optimum temperature for purging and vacuum cleaning. The data indicate that the purging for 20 hours with the above N2 flow can accomplish the same level of cleaning provided by the vacuum with the blankets at 25 deg C for 20 hours, In both cases, the rate of outgassing after 20 hours is reduced by 3 orders of magnitude, and the weight losses are in the range of 10E-4 gr/sq cm. Equivalent mass loss time constants, regained mass in air as a function of time, and other parameters were obtained for those blankets.

Spacecraft thermal blanket cleaning - Vacuum baking or gaseous flow purging

NASA Technical Reports Server (NTRS)

Scialdone, John J.

1992-01-01

The mass losses and the outgassing rates per unit area of three thermal blankets consisting of various combinations of Mylar and Kapton, with interposed Dacron nets, were measured with a microbalance using two methods. The blankets at 25 deg C were either outgassed in vacuum for 20 hours, or were purged with a dry nitrogen flow of 3 cu. ft. per hour at 25 deg C for 20 hours. The two methods were compared for their effectiveness in cleaning the blankets for their use in space applications. The measurements were carried out using blanket strips and rolled-up blanket samples fitting the microbalance cylindrical plenum. Also, temperature scanning tests were carried out to indicate the optimum temperature for purging and vacuum cleaning. The data indicate that the purging for 20 hours with the above N2 flow can accomplish the same level of cleaning provided by the vacuum with the blankets at 25 deg C for 20 hours. In both cases, the rate of outgassing after 20 hours is reduced by 3 orders of magnitude, and the weight losses are in the range of 10E-4 gr/sq cm. Equivalent mass loss time constants, regained mass in air as a function of time, and other parameters were obtained for those blankets.

KSC-04pd0615

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- A closeup of the stitching being done on pieces of insulation blankets inside the ring that fits in the nose cap of Discovery. The blankets consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance.

Space Station Freedom solar array containment box mechanisms

NASA Technical Reports Server (NTRS)

Johnson, Mark E.; Haugen, Bert; Anderson, Grant

1994-01-01

Space Station Freedom will feature six large solar arrays, called solar array wings, built by Lockheed Missiles & Space Company under contract to Rockwell International, Rocketdyne Division. Solar cells are mounted on flexible substrate panels which are hinged together to form a 'blanket.' Each wing is comprised of two blankets supported by a central mast, producing approximately 32 kW of power at beginning-of-life. During launch, the blankets are fan-folded and compressed to 1.5 percent of their deployed length into containment boxes. This paper describes the main containment box mechanisms designed to protect, deploy, and retract the solar array blankets: the latch, blanket restraint, tension, and guidewire mechanisms.

KSC-04pd0624

NASA Image and Video Library

2004-03-25

KENNEDY SPACE CENTER, FLA. -- Damon Petty, with United Space Alliance, removes a piece of insulation blanket from an “oven” after heat cleaning. The blankets fit inside the nose cap of an orbiter. They consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04pd0626

NASA Image and Video Library

2004-03-25

KENNEDY SPACE CENTER, FLA. -- Damon Petty, with United Space Alliance, covers another insulation blanket in the “oven” prior to heat cleaning. The blankets fit inside the nose cap of an orbiter. They consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04pd0623

NASA Image and Video Library

2004-03-25

KENNEDY SPACE CENTER, FLA. -- Damon Petty, with United Space Alliance, places pieces of insulation blanket into an “oven” for heat cleaning. The blankets fit inside the nose cap of an orbiter. They consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04pd0628

NASA Image and Video Library

2004-03-25

KENNEDY SPACE CENTER, FLA. -- Damon Petty, with United Space Alliance, gets ready to place insulation blankets on the shelf after they have been heated. The blankets fit inside the nose cap of an orbiter. They consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04pd0625

NASA Image and Video Library

2004-03-25

KENNEDY SPACE CENTER, FLA. -- Damon Petty, with United Space Alliance, removes another insulation blanket from a shelf prior to heat cleaning and waterproofing. The blankets fit inside the nose cap of an orbiter. They consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04pd0627

NASA Image and Video Library

2004-03-25

KENNEDY SPACE CENTER, FLA. -- Damon Petty, with United Space Alliance, prepares the cover of another insulation blanket in the “oven” prior to heat cleaning. The blankets fit inside the nose cap of an orbiter. They consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04pd0622

NASA Image and Video Library

2004-03-25

KENNEDY SPACE CENTER, FLA. -- Damon Petty, with United Space Alliance, removes an insulation blanket from a shelf prior to heat cleaning and waterproofing. The blankets fit inside the nose cap of an orbiter. They consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04pd0614

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- United Space Alliance workers Michael Williams and Ginger Morrison stitch together pieces of insulation blankets inside the ring that fits in the nose cap of Discovery. The blankets consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance.

KSC-04pd0613

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- United Space Alliance workers Ginger Morrison and Michael Williams stitch together pieces of insulation blankets inside the ring that fits in the nose cap of Discovery. The blankets consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04PD-0613

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- United Space Alliance workers Ginger Morrison and Michael Williams stitch together pieces of insulation blankets inside the ring that fits in the nose cap of Discovery. The blankets consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches.

KSC-04PD-0616

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- United Space Alliance workers Ginger Morrison and Michael Williams stitch together pieces of insulation blankets inside the ring that fits in the nose cap of Discovery. The blankets consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches. The blanket is through- stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance.

KSC-04pd0616

NASA Image and Video Library

2004-03-24

KENNEDY SPACE CENTER, FLA. -- United Space Alliance workers Ginger Morrison and Michael Williams stitch together pieces of insulation blankets inside the ring that fits in the nose cap of Discovery. The blankets consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches. The blanket is through-stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance.

KSC-04PD-0614

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- United Space Alliance workers Michael Williams and Ginger Morrison stitch together pieces of insulation blankets inside the ring that fits in the nose cap of Discovery. The blankets consist of layered, pure silica felt sandwiched between a layer of silica fabric (the hot side) and a layer of S-Glass fabric. The blankets are semi-rigid and can be made as large as 30 inches by 30 inches. The blanket is through- stitched with pure silica thread in a 1-inch grid pattern. After fabrication, the blanket is bonded directly to the vehicle structure and finally coated with a high purity silica coating that improves erosion resistance.

48 CFR 613.303 - Blanket purchase agreements (BPAs).

Code of Federal Regulations, 2010 CFR

2010-10-01

... 48 Federal Acquisition Regulations System 4 2010-10-01 2010-10-01 false Blanket purchase agreements (BPAs). 613.303 Section 613.303 Federal Acquisition Regulations System DEPARTMENT OF STATE....303 Blanket purchase agreements (BPAs). ...

48 CFR 1313.303 - Blanket Purchase Agreements (BPAs).

Code of Federal Regulations, 2010 CFR

2010-10-01

... 48 Federal Acquisition Regulations System 5 2010-10-01 2010-10-01 false Blanket Purchase Agreements (BPAs). 1313.303 Section 1313.303 Federal Acquisition Regulations System DEPARTMENT OF COMMERCE....303 Blanket Purchase Agreements (BPAs). ...

48 CFR 13.303 - Blanket purchase agreements (BPAs).

Code of Federal Regulations, 2010 CFR

2010-10-01

... 48 Federal Acquisition Regulations System 1 2010-10-01 2010-10-01 false Blanket purchase agreements (BPAs). 13.303 Section 13.303 Federal Acquisition Regulations System FEDERAL ACQUISITION... Methods 13.303 Blanket purchase agreements (BPAs). ...

Epoxy blanket protects milled part during explosive forming

NASA Technical Reports Server (NTRS)

1966-01-01

Epoxy blanket protects chemically milled or machined sections of large, complex structural parts during explosive forming. The blanket uniformly covers all exposed surfaces and fills any voids to support and protect the entire part.

Design optimization of first wall and breeder unit module size for the Indian HCCB blanket module

NASA Astrophysics Data System (ADS)

Deepak, SHARMA; Paritosh, CHAUDHURI

2018-04-01

The Indian test blanket module (TBM) program in ITER is one of the major steps in the Indian fusion reactor program for carrying out the R&D activities in the critical areas like design of tritium breeding blankets relevant to future Indian fusion devices (ITER relevant and DEMO). The Indian Lead–Lithium Cooled Ceramic Breeder (LLCB) blanket concept is one of the Indian DEMO relevant TBM, to be tested in ITER as a part of the TBM program. Helium-Cooled Ceramic Breeder (HCCB) is an alternative blanket concept that consists of lithium titanate (Li2TiO3) as ceramic breeder (CB) material in the form of packed pebble beds and beryllium as the neutron multiplier. Specifically, attentions are given to the optimization of first wall coolant channel design and size of breeder unit module considering coolant pressure and thermal loads for the proposed Indian HCCB blanket based on ITER relevant TBM and loading conditions. These analyses will help proceeding further in designing blankets for loads relevant to the future fusion device.

Multiplier, moderator, and reflector materials for lithium-vanadium fusion blankets.

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

Gohar, Y.; Smith, D. L.

1999-10-07

The self-cooled lithium-vanadium fusion blanket concept has several attractive operational and environmental features. In this concept, liquid lithium works as the tritium breeder and coolant to alleviate issues of coolant breeder compatibility and reactivity. Vanadium alloy (V-4Cr-4Ti) is used as the structural material because of its superior performance relative to other alloys for this application. However, this concept has poor attenuation characteristics and energy multiplication for the DT neutrons. An advanced self-cooled lithium-vanadium fusion blanket concept has been developed to eliminate these drawbacks while maintaining all the attractive features of the conventional concept. An electrical insulator coating for the coolantmore » channels, spectral shifter (multiplier, and moderator) and reflector were utilized in the blanket design to enhance the blanket performance. In addition, the blanket was designed to have the capability to operate at high loading conditions of 2 MW/m{sup 2} surface heat flux and 10 MW/m{sup 2} neutron wall loading. This paper assesses the spectral shifter and the reflector materials and it defines the technological requirements of this advanced blanket concept.« less

The Markov blankets of life: autonomy, active inference and the free energy principle

PubMed Central

Palacios, Ensor; Friston, Karl; Kiverstein, Julian

2018-01-01

This work addresses the autonomous organization of biological systems. It does so by considering the boundaries of biological systems, from individual cells to Home sapiens, in terms of the presence of Markov blankets under the active inference scheme—a corollary of the free energy principle. A Markov blanket defines the boundaries of a system in a statistical sense. Here we consider how a collective of Markov blankets can self-assemble into a global system that itself has a Markov blanket; thereby providing an illustration of how autonomous systems can be understood as having layers of nested and self-sustaining boundaries. This allows us to show that: (i) any living system is a Markov blanketed system and (ii) the boundaries of such systems need not be co-extensive with the biophysical boundaries of a living organism. In other words, autonomous systems are hierarchically composed of Markov blankets of Markov blankets—all the way down to individual cells, all the way up to you and me, and all the way out to include elements of the local environment. PMID:29343629

Multiplier, moderator, and reflector materials for advanced lithium?vanadium fusion blankets

NASA Astrophysics Data System (ADS)

Gohar, Y.; Smith, D. L.

2000-12-01

The self-cooled lithium-vanadium fusion blanket concept has several attractive operational and environmental features. In this concept, liquid lithium works as the tritium breeder and coolant to alleviate issues of coolant breeder compatibility and reactivity. Vanadium alloy (V-4Cr-4Ti) is used as the structural material because of its superior performance relative to other alloys for this application. However, this concept has poor attenuation characteristics and energy multiplication for the DT neutrons. An advanced self-cooled lithium-vanadium fusion blanket concept has been developed to eliminate these drawbacks while maintaining all the attractive features of the conventional concept. An electrical insulator coating for the coolant channels, spectral shifter (multiplier, and moderator) and reflector were utilized in the blanket design to enhance the blanket performance. In addition, the blanket was designed to have the capability to operate at average loading conditions of 2 MW/m 2 surface heat flux and 10 MW/m 2 neutron wall loading. This paper assesses the spectral shifter and the reflector materials and it defines the technological requirements of this advanced blanket concept.

Design and Development of an In-Space Deployable Sun Shield for the Atlas Centaur

NASA Technical Reports Server (NTRS)

Dew, Michael; Allwein, Kirk; Kutter, Bernard; Ware, Joanne; Lin, John; Madlangbayan, Albert; Willey, Cliff; Pitchford, Brian; O'Neil, Gary

2008-01-01

The Centaur, by virtue of its use of high specific-impulse (Isp) LO2/LH2 propellants, has initial mass-to-orbit launch requirements less than half of those upper stages using storable propellants. That is, for Earth escape or GSO missions the Centaur is half the launch weight of a storable propellant upper stage. A drawback to the use of Liquid oxygen and liquid hydrogen, at 90 K and 20 K respectively, over storable propellants is the necessity of efficient cryogen storage techniques that minimize boil-off from thermal radiation in space. Thermal blankets have been used successfully to shield both the Atlas Centaur and Titan Centaur. These blankets are protected from atmospheric air loads during launch by virtue of the fact that the Centaur is enclosed within the payload fairing. The smaller Atlas V vehicle, the Atlas 400, has the Centaur exposed to the atmosphere during launch, and therefore, to date has not flown with thermal blankets shielding the Centaur. A design and development effort is underway to fly a thermal shield on the Atlas V 400 vehicle that is not put in place until after the payload fairing jettisons. This can be accomplished by the use of an inflatable and deployable thermal blanket referred to as the Centaur Sun Shield (CSS). The CSS design is also scalable for use on a Delta upper stage, and the technology potentially could be used for telescope shades, re-entry shields, solar sails and propellant depots. A Phase I effort took place during 2007 in a partnership between ULA and ILC Dover which resulted in a deployable proof-of-concept Sun Shield being demonstrated at a test facility in Denver. A Phase H effort is underway during 2008 with a partnership between ULA, ILC, NASA Glenn Research Center (GRC) and NASA Kennedy Space Center (KSC) to define requirements, determine materials and fabrication techniques, and to test components in a vacuum chamber at cold temperatures. This paper describes the Sun Shield development work to date, and the future plans leading up to a flight test in the 2011 time frame.

KSC-04pd0597

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers prepare for contact of NASA’s MESSENGER spacecraft with a test stand. Once in place, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

KSC-04pd0599

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers verify the correct placement of NASA’s MESSENGER spacecraft on a test stand. Once in place, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

KSC-04pd0594

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers prepare to move NASA’s MESSENGER spacecraft onto a test stand using an overhead crane. There, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

KSC-04pd0598

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers check for the correct alignment of NASA’s MESSENGER spacecraft as it is lowered onto a test stand. Once in place, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

KSC-04pd0595

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers lower NASA’s MESSENGER spacecraft onto a test stand using an overhead crane. Once in place, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

KSC-04pd0603

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, the attachment of NASA’s MESSENGER spacecraft to a test stand is complete. The spacecraft is now ready for employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, to begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

KSC-04pd0596

NASA Image and Video Library

2004-03-22

KENNEDY SPACE CENTER, FLA. -- At the Astrotech Space Operations processing facilities, workers monitor NASA’s MESSENGER spacecraft as it is lowered onto a test stand by an overhead crane. Once in place, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will begin final processing for launch, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be launched aboard a Boeing Delta II rocket no earlier than July 30 on a six-year mission to study the planet Mercury.

Data bases for LDEF results

NASA Technical Reports Server (NTRS)

Bohnhoff-Hlavacek, Gail

1993-01-01

The Long Duration Exposure Facility (LDEF) carried 57 experiments and 10,000 specimens for some 200 LDEF experiment investigators. The external surface of LDEF had a large variety of materials exposed to the space environment which were tested preflight, during flight, and post flight. Thermal blankets, optical materials, thermal control paints, aluminum, and composites are among the materials flown. The investigations have produced an abundance of analysis results. One of the responsibilities of the Boeing Support Contract, Materials and Systems Special Investigation Group, is to collate and compile that information into an organized fashion. The databases developed at Boeing to accomplish this task is described.

OA-7 Nano-rack Installation

NASA Image and Video Library

2017-02-27

Inside the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center in Florida, a technician adjusts the thermal blankets around the area where several Nanoracks will be installed on the exterior of the Orbital ATK Cygnus pressurized cargo module. The Orbital ATK CRS-7 commercial resupply services mission to the International Space Station is scheduled to launch atop a United Launch Alliance Atlas V rocket from Space Launch Complex 41 at Cape Canaveral Air Force Station no earlier than March 21, 2017. Cygnus will deliver 7,600 pounds of supplies, equipment and scientific research materials to the space station.

KSC-04pd0965

NASA Image and Video Library

2004-04-28

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility remove Ground Support Equipment used to install Discovery’s nose cap on Friday. The nose cap had been removed from the vehicle in the summer of 2003 and returned to the vendor, where it underwent numerous forms of Non-Destructive Evaluation. These tests included X-ray, ultrasound and eddy current to ensure its structural integrity prior to installation on the vehicle. The nose cap was also recoated. Once returned to KSC, new Thermal Protection System blankets were assembled inside of the nose cap and thermography was performed prior to installation on the orbiter.

KSC-04pd0964

NASA Image and Video Library

2004-04-28

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility get ready to remove Ground Support Equipment used to install Discovery’s nose cap on Friday. The nose cap had been removed from the vehicle in the summer of 2003 and returned to the vendor, where it underwent numerous forms of Non-Destructive Evaluation. These tests included X-ray, ultrasound and eddy current to ensure its structural integrity prior to installation on the vehicle. The nose cap was also recoated. Once returned to KSC, new Thermal Protection System blankets were assembled inside of the nose cap and thermography was performed prior to installation on the orbiter.

Surface Catalysis and Characterization of Proposed Candidate TPS for Access-to-Space Vehicles

NASA Technical Reports Server (NTRS)

Stewart, David A.

1997-01-01

Surface properties have been obtained on several classes of thermal protection systems (TPS) using data from both side-arm-reactor and arc-jet facilities. Thermochemical stability, optical properties, and coefficients for atom recombination were determined for candidate TPS proposed for single-stage-to-orbit vehicles. The systems included rigid fibrous insulations, blankets, reinforced carbon carbon, and metals. Test techniques, theories used to define arc-jet and side-arm-reactor flow, and material surface properties are described. Total hemispherical emittance and atom recombination coefficients for each candidate TPS are summarized in the form of polynomial and Arrhenius expressions.

KSC-04PD-1682

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, workers check the fit of the nose cap (right) after installation on the orbiter Atlantis. The nose cap was removed from the vehicle in May and sent back to the vendor for thorough Non- Destructive Engineering evaluation and recoating. Thermography was also performed to check for internal flaws. This procedure uses high intensity light to heat areas that are immediately scanned with an infrared camera. White Thermal Protection System blankets were reinstalled on the nose cap before installation. Processing continues on Atlantis for its future mission to the International Space Station.

Detail view of the leading and top edge of the ...

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

Detail view of the leading and top edge of the vertical stabilizer of the Orbiter Discovery showing the thermal protection system components with the white Advanced Flexible Reusable Surface Insulation (AFRSI) blanket and the black High-temperature Reusable Surface Insulation (HRSI) tiles along the outer edges. The marks seen on the HRSI tiles are injection point marks and holes for the application of waterproofing material. This view was taken from a service platform in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

KSC-04PD-0706

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. -- United Space Alliance (USA) technicians check the placement of the thermal blanket insulation inside Discoverys nose cap, which is under a protective cover and seated on a work stand above them. On the floor at left is Terry OShea; with his back to the camera is Justin Hopmann; standing underneath the work stand is Mike Williams. On the left of the work stand is Ginger Morrison. The work is being done in a low bay area outside the Orbiter Processing Facility. Discovery is the orbiter named as the vehicle for Return to Flight with mission STS-114.

KSC-04pd0706

NASA Image and Video Library

2004-04-05

KENNEDY SPACE CENTER, FLA. -- United Space Alliance (USA) technicians check the placement of the thermal blanket insulation inside Discovery’s nose cap, which is under a protective cover and seated on a work stand above them. On the floor at left is Terry O’Shea; with his back to the camera is Justin Hopmann; standing underneath the work stand is Mike Williams. On the left of the work stand is Ginger Morrison. The work is being done in a low bay area outside the Orbiter Processing Facility. Discovery is the orbiter named as the vehicle for Return to Flight with mission STS-114.

48 CFR 213.303 - Blanket purchase agreements (BPAs).

Code of Federal Regulations, 2010 CFR

2010-10-01

... 48 Federal Acquisition Regulations System 3 2010-10-01 2010-10-01 false Blanket purchase agreements (BPAs). 213.303 Section 213.303 Federal Acquisition Regulations System DEFENSE ACQUISITION... PROCEDURES Simplified Acquisition Methods 213.303 Blanket purchase agreements (BPAs). ...

"Easy-on, Easy-off" Blanket Fastener

NASA Technical Reports Server (NTRS)

Kolecki, Ronald E.; Clatterbuck, Carroll H.

1992-01-01

Fasteners hold flexible blanket on set of posts on supporting structure. Disk of silicone rubber cast on disk of Mylar, fastened to blanket and press-fit over post to nest securely in groove. No tools needed for installation or removal.

Analysis of the ORNL/TSF GCFR Grid-Plate Shield Design Confirmation Experiment

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

Slater, C.O.; Cramer, S.N.; Ingersoll, D.T.

1979-08-01

The results of the analysis of the GCFR Grid-Plate Shield Design Confirmation Experiment are presented. The experiment, performed at the ORNL Tower Shielding Facility, was designed to test the adequacy of methods and data used in the analysis of the GCFR design. In particular, the experiment tested the adequacy of methods to calculate: (1) axial neutron streaming in the GCFR core and axial blanket, (2) the amount and location of the maximum fast-neutron exposure to the grid plate, and (3) the neutron source leaving the top of the grid plate and entering the upper plenum. Other objectives of the experimentmore » were to verify the grid-plate shielding effectiveness and to assess the effects of fuel-pin and subassembly spacing on radiation levels in the GCFR. The experimental mockups contained regions representing the GCFR core/blanket region, the grid-plate shield section, and the grid plate. Most core design options were covered by allowing: (1) three different spacings between fuel subassemblies, (2) two different void fractions within a subassembly by variation of the number of fuel pins, and (3) a mockup of a control-rod channel.« less

Parameter Study of the LIFE Engine Nuclear Design

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

Kramer, K J; Meier, W R; Latkowski, J F

2009-07-10

LLNL is developing the nuclear fusion based Laser Inertial Fusion Energy (LIFE) power plant concept. The baseline design uses a depleted uranium (DU) fission fuel blanket with a flowing molten salt coolant (flibe) that also breeds the tritium needed to sustain the fusion energy source. Indirect drive targets, similar to those that will be demonstrated on the National Ignition Facility (NIF), are ignited at {approx}13 Hz providing a 500 MW fusion source. The DU is in the form of a uranium oxycarbide kernel in modified TRISO-like fuel particles distributed in a carbon matrix forming 2-cm-diameter pebbles. The thermal power ismore » held at 2000 MW by continuously varying the 6Li enrichment in the coolants. There are many options to be considered in the engine design including target yield, U-to-C ratio in the fuel, fission blanket thickness, etc. Here we report results of design variations and compare them in terms of various figures of merit such as time to reach a desired burnup, full-power years of operation, time and maximum burnup at power ramp down and the overall balance of plant utilization.« less

Hierarchical Markov blankets and adaptive active inference. Comment on "Answering Schrödinger's question: A free-energy formulation" by Maxwell James Désormeau Ramstead et al.

NASA Astrophysics Data System (ADS)

Kirchhoff, Michael

2018-03-01

Ramstead MJD, Badcock PB, Friston KJ. Answering Schrödinger's question: A free-energy formulation. Phys Life Rev 2018. https://doi.org/10.1016/j.plrev.2017.09.001 [this issue] motivate a multiscale characterisation of living systems in terms of hierarchically structured Markov blankets - a view of living systems as comprised of Markov blankets of Markov blankets [1-4]. It is effectively a treatment of what life is and how it is realised, cast in terms of how Markov blankets of living systems self-organise via active inference - a corollary of the free energy principle [5-7].

Low RF Reflectivity Spacecraft Thermal Blanket by Using High-Impedance Surface Absorbers

NASA Astrophysics Data System (ADS)

Costa, F.; Monorchio, A.; Carrubba, E.; Zolesi, V.

2012-05-01

A technique for designing a low-RF reflectivity thermal blanket is presented. Multi-layer insulation (MLI) blankets are employed to stabilize the temperature on spacecraft unit but they can be responsible of passive intermodulation products and high-mutual coupling between antennas since they are realized with metallic materials. The possibility to replace the last inner layer of a MLI blanket with an ultra-thin absorbing layer made of high-impedance surface absorber is discussed.

Improved Acoustic Blanket Developed and Tested

NASA Technical Reports Server (NTRS)

1996-01-01

Acoustic blankets are used in the payload fairing of expendable launch vehicles to reduce the fairing's interior acoustics and the subsequent vibration response of the spacecraft. The Cassini spacecraft, to be launched on a Titan IV in October 1997, requires acoustic levels lower than those provided by the standard Titan IV blankets. Therefore, new acoustic blankets were recently developed and tested to reach NASA's goal of reducing the Titan IV acoustic environment to the allowable levels for the Cassini spacecraft.

High temperature lined conduits, elbows and tees

DOEpatents

De Feo, Angelo; Drewniany, Edward

1982-01-01

A high temperature lined conduit comprising, a liner, a flexible insulating refractory blanket around and in contact with the liner, a pipe member around the blanket and spaced therefrom, and castable rigid refractory material between the pipe member and the blanket. Anchors are connected to the inside diameter of the pipe and extend into the castable material. The liner includes male and female slip joint ends for permitting thermal expansion of the liner with respect to the castable material and the pipe member. Elbows and tees of the lined conduit comprise an elbow liner wrapped with insulating refractory blanket material around which is disposed a spaced elbow pipe member with castable refractory material between the blanket material and the elbow pipe member. A reinforcing band is connected to the elbow liner at an intermediate location thereon from which extend a plurality of hollow tubes or pins which extend into the castable material to anchor the lined elbow and permit thermal expansion. A method of fabricating the high temperature lined conduit, elbows and tees is also disclosed which utilizes a polyethylene layer over the refractory blanket after it has been compressed to maintain the refractory blanket in a compressed condition until the castable material is in place. Hot gases are then directed through the interior of the liner for evaporating the polyethylene and setting the castable material which permits the compressed blanket to come into close contact with the castable material.

47 CFR 73.318 - FM blanketing interference.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 47 Telecommunication 4 2011-10-01 2011-10-01 false FM blanketing interference. 73.318 Section 73.318 Telecommunication FEDERAL COMMUNICATIONS COMMISSION (CONTINUED) BROADCAST RADIO SERVICES RADIO BROADCAST SERVICES FM Broadcast Stations § 73.318 FM blanketing interference. Areas adjacent to the...

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

Not Available

Three solid-breeder water-cooled blanket concepts have been developed for ITER based on a multilayer configuration. The primary difference among the concepts is in the fabricated form of breeder and multiplier. All the concepts have beryllium for neutron multiplication and solid-breeder temperature control. The blanket design does not use helium gaps or insulator material to control the solid breeder temperature. Lithium oxide (Li{sub 2}O) and lithium zirconate (Li{sub 2}ZrO{sub 3}) are the primary and the backup breeder materials, respectively. The lithium-6 enrichment is 95%. The use of high lithium-6 enrichment reduces the solid breeder volume required in the blanket and consequentlymore » the total tritium inventory in the solid breeder material. Also, it increases the blanket capability to accommodate power variation. The multilayer blanket configuration can accommodate up to a factor of two change in the neutron wall loading without violating the different design guidelines. The blanket material forms are sintered products and packed bed of small pebbles. The first concept has a sintered product material (blocks) for both the beryllium multiplier and the solid breeder. The second concept, the common ITER blanket, uses a packed bed breeder and beryllium blocks. The last concept is similar to the first except for the first and the last beryllium zones. Two small layers of beryllium pebbles are located behind the first wall and the back of the last beryllium zone to reduce the total inventory of the beryllium material and to improve the blanket performance. The design philosophy adopted for the blanket is to produce the necessary tritium required for the ITER operation and to operate at power reactor conditions as much as possible. Also, the reliability and the safety aspects of the blanket are enhanced by using low-pressure water coolant and the separation of the tritium purge flow from the coolant system by several barriers.« less

Development of a new multi-layer insulation blanket with non-interlayer-contact spacer for space cryogenic mission

NASA Astrophysics Data System (ADS)

Miyakita, Takeshi; Hatakenaka, Ryuta; Sugita, Hiroyuki; Saitoh, Masanori; Hirai, Tomoyuki

2014-11-01

For conventional Multi-Layer Insulation (MLI) blankets, it is difficult to control the layer density and the thermal insulation performance degrades due to the increase in conductive heat leak through interlayer contacts. At low temperatures, the proportion of conductive heat transfer through MLI blankets is large compared to that of radiative heat transfer, hence the decline in thermal insulation performance is significant. A new type of MLI blanket using new spacers; the Non-Interlayer-Contact Spacer MLI (NICS MLI) has been developed. This new MLI blanket uses small discrete spacers and can exclude uncertain interlayer contact between films. It is made of polyetheretherketone (PEEK) making it suitable for space use. The cross-sectional area to length ratio of the spacer is 1.0 × 10-5 m with a 10 mm diameter and 4 mm height. The insulation performance is measured with a boil-off calorimeter. Because the NICS MLI blanket can exclude uncertain interlayer contact, the test results showed good agreement with estimations. Furthermore, the NICS MLI blanket shows significantly good insulation performance (effective emissivity is 0.0046 at ordinary temperature), particularly at low temperatures, due to the high thermal resistance of this spacer.

Surge current and electron swarm tunnel tests of thermal blanket and ground strap materials

NASA Technical Reports Server (NTRS)

Hoffmaster, D. K.; Inouye, G. T.; Sellen, J. M., Jr.

1977-01-01

The results are described of a series of current conduction tests with a thermal control blanket to which grounding straps have been attached. The material and the ground strap attachment procedure are described. The current conduction tests consisted of a surge current examination of the ground strap and a dilute flow, energetic electron deposition and transport through the bulk of the insulating film of this thermal blanket material. Both of these test procedures were used previously with thermal control blanket materials.

Retractable Sun Shade

NASA Technical Reports Server (NTRS)

Frank, A.; Derespinis, S. F.; Mockovciak, John, Jr.

1986-01-01

Window-shade type spring roller contains blanket, taken up by rotating cylindrical frame and held by frame over area to be shaded. Blanket made of tough, opaque polyimide material. Readily unfurled by mechanism to protect space it encloses from Sun. Blanket forms arched canopy over space and allows full access to it from below. When shading not needed, retracted mechanism stores blanket compactly. Developed for protecting sensitive Space Shuttle payloads from direct sunlight while cargo-bay doors open. Adapted to shading of greenhouses, swimming pools, and boats.

Thin Thermal-Insulation Blankets for Very High Temperatures

NASA Technical Reports Server (NTRS)

Choi, Michael K.

2003-01-01

Thermal-insulation blankets of a proposed type would be exceptionally thin and would endure temperatures up to 2,100 C. These blankets were originally intended to protect components of the NASA Solar Probe spacecraft against radiant heating at its planned closest approach to the Sun (a distance of 4 solar radii). These blankets could also be used on Earth to provide thermal protection in special applications (especially in vacuum chambers) for which conventional thermal-insulation blankets would be too thick or would not perform adequately. A blanket according to the proposal (see figure) would be made of molybdenum, titanium nitride, and carbon- carbon composite mesh, which melt at temperatures of 2,610, 2,930, and 2,130 C, respectively. The emittance of molybdenum is 0.24, while that of titanium nitride is 0.03. Carbon-carbon composite mesh is a thermal insulator. Typically, the blanket would include 0.25-mil (.0.00635-mm)-thick hot-side and cold-side cover layers of molybdenum. Titanium nitride would be vapor-deposited on both surfaces of each cover layer. Between the cover layers there would be 10 inner layers of 0.15-mil (.0.0038-mm)-thick molybdenum with vapor-deposited titanium nitride on both sides of each layer. The thickness of each titanium nitride coat would be about 1,000 A. The cover and inner layers would be interspersed with 0.25-mil (0.00635-mm)-thick layers of carbon-carbon composite mesh. The blanket would have total thickness of 4.75 mils (approximately equal to 0.121 mm) and an areal mass density of 0.7 kilograms per square meter. One could, of course, increase the thermal- insulation capability of the blanket by increasing number of inner layers (thereby unavoidably increasing the total thickness and mass density).

Cassini/Titan-4 Acoustic Blanket Development and Testing

NASA Technical Reports Server (NTRS)

Hughes, William O.; McNelis, Anne M.

1996-01-01

NASA Lewis Research Center recently led a multi-organizational effort to develop and test verify new acoustic blankets. These blankets support NASA's goal in reducing the Titan-4 payload fairing internal acoustic environment to allowable levels for the Cassini spacecraft. To accomplish this goal a two phase acoustic test program was utilized. Phase One consisted of testing numerous blanket designs in a flat panel configuration. Phase Two consisted of testing the most promising designs out of Phase One in a full scale cylindrical payload fairing. This paper will summarize this highly successful test program by providing the rationale and results for each test phase, the impacts of this testing on the Cassini mission, as well as providing some general information on blanket designs.

Application of the aqueous self-cooled blanket concept to fusion reactors

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

Deutsch, L.; Steiner, D.; Embrechts, M.J.

1986-01-01

The development of a reliable, safe, and economically attractive tritium breeding blanket is an essential requirement in the path to commercial fusion power. The primary objective of the recently completed Blanket Comparison and Selection Study (BCSS) was to evaluate previously proposed concepts, and thereby identify a limited number of preferred options that would provide the focus for an R and D program. The water-cooled concepts in the BCSS scored relatively low. We consider it prudent that a promising water-cooled blanket concept be included in this program since nearly all power producing reactors currently rely on water technology. It is inmore » this context that we propose the novel water-cooled blanket concept described herein.« less

KSC-08pd2307

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane is attached to the Multi-Use Lightweight Equipment, or MULE, carrier to moved the carrier to another stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2308

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane lifts the Multi-Use Lightweight Equipment, or MULE, carrier from a mobile platform to move it to another stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2309

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane lifts the Multi-Use Lightweight Equipment, or MULE, carrier from a mobile platform to move it to another stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2310

NASA Image and Video Library

2008-08-06

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane lifts the Multi-Use Lightweight Equipment, or MULE, carrier from a mobile platform to move it to another stand in the high bay. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. Photo credit: NASA/Jack Pfaller

KSC-08pd2295

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, an overhead crane is attached to the shipping container with the Multi-Use Lightweight Equipment (MULE) carrier inside. The cover will be removed. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-08pd2299

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – In the Payload Hazardous Servicing Facility at NASA's Kennedy Space Center, workers in the background detach the crane from the cover of the shipping container removed from the Multi-Use Lightweight Equipment (MULE) carrier in the foreground. The MULE is part of the payload for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-04pd1791

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - United Space Alliance worker Bab Jarosz works with the 30-needle sewing machines from the Thermal Protection System Facility (TPSF). A temporary tile shop has been set up in the RLV hangar at KSC after equipment was removed from the hurricane-ravaged facility. The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-04pd1790

NASA Image and Video Library

2004-09-14

KENNEDY SPACE CENTER, FLA. - United Space Alliance worker Bab Jarosz works with the 30-needle sewing machines from the Thermal Protection System Facility (TPSF). A temporary tile shop has been set up in the RLV hangar at KSC after equipment was removed from the hurricane-ravaged facility. The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

The Structural Heat Intercept-Insulation-Vibration Evaluation Rig (SHIVER)

NASA Technical Reports Server (NTRS)

Johnson, W. L.; Zoeckler, J. G.; Best-Ameen, L. M.

2015-01-01

NASA is currently investigating methods to reduce the boil-off rate on large cryogenic upper stages. Two such methods to reduce the total heat load on existing upper stages are vapor cooling of the cryogenic tank support structure and integration of thick multilayer insulation systems to the upper stage of a launch vehicle. Previous efforts have flown a 2-layer MLI blanket and shown an improved thermal performance, and other efforts have ground-tested blankets up to 70 layers thick on tanks with diameters between 2 3 meters. However, thick multilayer insulation installation and testing in both thermal and structural modes has not been completed on a large scale tank. Similarly, multiple vapor cooled shields are common place on science payload helium dewars; however, minimal effort has gone into intercepting heat on large structural surfaces associated with rocket stages. A majority of the vapor cooling effort focuses on metallic cylinders called skirts, which are the most common structural components for launch vehicles. In order to provide test data for comparison with analytical models, a representative test tank is currently being designed to include skirt structural systems with integral vapor cooling. The tank is 4 m in diameter and 6.8 m tall to contain 5000 kg of liquid hydrogen. A multilayer insulation system will be designed to insulate the tank and structure while being installed in a representative manner that can be extended to tanks up to 10 meters in diameter. In order to prove that the insulation system and vapor cooling attachment methods are structurally sound, acoustic testing will also be performed on the system. The test tank with insulation and vapor cooled shield installed will be tested thermally in the B2 test facility at NASAs Plumbrook Station both before and after being vibration tested at Plumbrooks Space Power Facility.

KENNEDY SPACE CENTER, FLA. - Shipped in an air-conditioned transportation van from NASA’s Goddard Space Flight Center in Greenbelt, Md., NASA’s MESSENGER spacecraft, the first Mercury orbiter, arrives at the Astrotech Space Operations processing facilities near KSC. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be offloaded and taken into a high bay clean room. After the spacecraft is removed from its shipping container, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

NASA Image and Video Library

2004-03-10

KENNEDY SPACE CENTER, FLA. - Shipped in an air-conditioned transportation van from NASA’s Goddard Space Flight Center in Greenbelt, Md., NASA’s MESSENGER spacecraft, the first Mercury orbiter, arrives at the Astrotech Space Operations processing facilities near KSC. MESSENGER - short for MErcury Surface, Space ENvironment, GEochemistry and Ranging - will be offloaded and taken into a high bay clean room. After the spacecraft is removed from its shipping container, employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

Distributing Radiant Heat in Insulation Tests

NASA Technical Reports Server (NTRS)

Freitag, H. J.; Reyes, A. R.; Ammerman, M. C.

1986-01-01

Thermally radiating blanket of stepped thickness distributes heat over insulation sample during thermal vacuum testing. Woven of silicon carbide fibers, blanket spreads heat from quartz lamps evenly over insulation sample. Because of fewer blanket layers toward periphery of sample, more heat initially penetrates there for more uniform heat distribution.

18 CFR 284.402 - Blanket marketing certificates.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 18 Conservation of Power and Water Resources 1 2012-04-01 2012-04-01 false Blanket marketing certificates. 284.402 Section 284.402 Conservation of Power and Water Resources FEDERAL ENERGY REGULATORY... RELATED AUTHORITIES Certain Sales for Resale by Non-interstate Pipelines § 284.402 Blanket marketing...

18 CFR 284.402 - Blanket marketing certificates.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 18 Conservation of Power and Water Resources 1 2010-04-01 2010-04-01 false Blanket marketing certificates. 284.402 Section 284.402 Conservation of Power and Water Resources FEDERAL ENERGY REGULATORY... RELATED AUTHORITIES Certain Sales for Resale by Non-interstate Pipelines § 284.402 Blanket marketing...

18 CFR 284.402 - Blanket marketing certificates.

Code of Federal Regulations, 2013 CFR

2013-04-01

... 18 Conservation of Power and Water Resources 1 2013-04-01 2013-04-01 false Blanket marketing certificates. 284.402 Section 284.402 Conservation of Power and Water Resources FEDERAL ENERGY REGULATORY... RELATED AUTHORITIES Certain Sales for Resale by Non-interstate Pipelines § 284.402 Blanket marketing...

Stainless steel blanket concept for tokamaks

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

Karbowski, J.S.; Lee, A.Y.; Prevenslik, T.V.

1979-01-25

The purpose of this joint ORNL/Westinghouse Program is to develop a design concept for a tokamak reactor blanket system which satisfies engineering requirements for a utility environment. While previous blanket studies have focused primarily on performance issues (thermal, neutronic, and structural), this study has emphasized consideration of reliability, fabricability, and lifetime.

48 CFR 313.303-5 - Purchases under blanket purchase agreements.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 48 Federal Acquisition Regulations System 4 2010-10-01 2010-10-01 false Purchases under blanket purchase agreements. 313.303-5 Section 313.303-5 Federal Acquisition Regulations System HEALTH AND HUMAN... Methods 313.303-5 Purchases under blanket purchase agreements. (e)(5) HHS personnel that sign delivery...

75 FR 51482 - Woven Electric Blankets From China

Federal Register 2010, 2011, 2012, 2013, 2014

2010-08-20

... From China Determination On the basis of the record \\1\\ developed in the subject investigation, the... injured by reason of imports from China of woven electric blankets, provided for in subheading 6301.10.00... notification of a preliminary determination by Commerce that imports of woven electric blankets from China were...

77 FR 31004 - Southern Natural Gas Company; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2012-05-24

... Natural Gas Company; Notice of Request Under Blanket Authorization Take notice that on May 9, 2012, Southern Natural Gas Company (Southern), 569 Brookwood Village, Suite 501, Birmingham, Alabama 35209, filed... Commission's regulations under the Natural Gas Act (NGA), and Southern's blanket certificate issued in Docket...

FAST NEUTRON REACTOR

DOEpatents

Soodak, H.; Wigner, E.P.

1961-07-25

A reactor comprising fissionable material in concentration sufficiently high so that the average neutron enengy within the reactor is at least 25,000 ev is described. A natural uranium blanket surrounds the reactor, and a moderating reflector surrounds the blanket. The blanket is thick enough to substantially eliminate flow of neutrons from the reflector.

77 FR 34876 - Airworthiness Directives; The Boeing Company

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-12

... (a flammable fluid leakage zone) or heat damage to the APU power feeder cable, insulation blankets... heat damage to the APU power feeder cable, insulation blankets, or pressure bulkhead. Relevant Service... feeder cable and heat damage of the insulation blanket adjacent to the clamp, a detailed inspection for...

18 CFR 33.1 - Applicability, definitions, and blanket authorizations.

Code of Federal Regulations, 2011 CFR

2011-04-01

... 18 Conservation of Power and Water Resources 1 2011-04-01 2011-04-01 false Applicability, definitions, and blanket authorizations. 33.1 Section 33.1 Conservation of Power and Water Resources FEDERAL... UNDER FEDERAL POWER ACT SECTION 203 § 33.1 Applicability, definitions, and blanket authorizations. (a...

HEAT GENERATION

DOEpatents

Imhoff, D.H.; Harker, W.H.

1963-12-01

Heat is generated by the utilization of high energy neutrons produced as by nuclear reactions between hydrogen isotopes in a blanket zone containing lithium, a neutron moderator, and uranium and/or thorium effective to achieve multtplicatton of the high energy neutron. The rnultiplied and moderated neutrons produced react further with lithium-6 to produce tritium in the blanket. Thermal neutron fissionable materials are also produced and consumed in situ in the blanket zone. The heat produced by the aggregate of the various nuclear reactions is then withdrawn from the blanket zone to be used or otherwise disposed externally. (AEC)

STS-98 crew takes part in Multi-Equipment Interface Test.

NASA Technical Reports Server (NTRS)

2000-01-01

In the Space Station Processing Facility, STS-98 Mission Specialist Thomas D. Jones (Ph.D.) looks up at the U.S. Lab Destiny with its debris shield blanket made of a material similar to that used in bullet-proof vests on Earth.. Along with Commander Kenneth D. Cockrell and Pilot Mark Polansky, Jones is taking part in a Multi-Equipment Interface Test (MEIT) on this significant element of the International Space Station. During the STS-98 mission, the crew will install the Lab on the station during a series of three space walks. The mission will provide the station with science research facilities and expand its power, life support and control capabilities. The U.S. Laboratory Module continues a long tradition of microgravity materials research, first conducted by Skylab and later Shuttle and Spacelab missions. Destiny is expected to be a major feature in future research, providing facilities for biotechnology, fluid physics, combustion, and life sciences research. The Lab is planned for launch aboard Space Shuttle Atlantis on the sixth ISS flight, currently targeted no earlier than Aug. 19, 2000.

KSC-00pp0181

NASA Image and Video Library

2000-02-03

KENNEDY SPACE CENTER, FLA. -- In the Space Station Processing Facility, STS-98 Mission Specialist Thomas D. Jones (Ph.D.) looks up at the U.S. Lab Destiny with its debris shield blanket made of a material similar to that used in bullet-proof vests on Earth. Along with Commander Kenneth D. Cockrell and Pilot Mark Polansky, Jones is taking part in a Multi-Equipment Interface Test (MEIT) on this significant element of the International Space Station. During the STS-98 mission, the crew will install the Lab on the Station during a series of three spacewalks. The mission will provide the Station with science research facilities and expand its power, life support and control capabilities. The U.S. Laboratory Module continues a long tradition of microgravity materials research, first conducted by Skylab and later Shuttle and Spacelab missions. Destiny is expected to be a major feature in future research, providing facilities for biotechnology, fluid physics, combustion and life sciences reseach. The Lab is planned for launch aboard Space Shuttle Atlantis on the sixth ISS flight, currently targeted no earlier than August 19, 2000.

KSC00pp0181

NASA Image and Video Library

2000-02-03

KENNEDY SPACE CENTER, FLA. -- In the Space Station Processing Facility, STS-98 Mission Specialist Thomas D. Jones (Ph.D.) looks up at the U.S. Lab Destiny with its debris shield blanket made of a material similar to that used in bullet-proof vests on Earth. Along with Commander Kenneth D. Cockrell and Pilot Mark Polansky, Jones is taking part in a Multi-Equipment Interface Test (MEIT) on this significant element of the International Space Station. During the STS-98 mission, the crew will install the Lab on the Station during a series of three spacewalks. The mission will provide the Station with science research facilities and expand its power, life support and control capabilities. The U.S. Laboratory Module continues a long tradition of microgravity materials research, first conducted by Skylab and later Shuttle and Spacelab missions. Destiny is expected to be a major feature in future research, providing facilities for biotechnology, fluid physics, combustion and life sciences reseach. The Lab is planned for launch aboard Space Shuttle Atlantis on the sixth ISS flight, currently targeted no earlier than August 19, 2000.

A torso model comparison of temperature preservation devices for use in the prehospital environment.

PubMed

Zasa, Michele; Flowers, Neil; Zideman, David; Hodgetts, Timothy J; Harris, Tim

2016-06-01

Hypothermia is an independent predictor of increased morbidity and mortality in patients with trauma. Several strategies and products have been developed to minimise patients' heat loss in the prehospital arena, but there is little evidence to inform the clinician concerning their effectiveness. We used a human torso model consisting of two 5.5-litre fluid bags to simultaneously compare four passive (space blanket, bubble wrap, Blizzard blanket, ambulance blanket) and one active (Ready-Heat II blanket) temperature preservation products. A torso model without any temperature preservation device provided a control. For each test, the torso models were warmed to 37°C and left outdoors. Core temperatures were recorded every 10 min for 1 h in total; tests were repeated 10 times. A significant difference in temperature was detected among groups at 30 and 60 min (F (1.29, 10.30)=103.58, p<0.001 and F (1.64, 14.78)=163.28, p<0.001, respectively). Mean temperature reductions (95% CI) after 1 h of environmental exposure were the following: 11.6 (10.3 to 12.9) °C in control group, 4.5 (3.9 to 5.1) °C in space blanket group, 3.6 (3 to 4.3) °C in bubble-wrap group, 2.1 (1.7 to 2.5) °C in Blizzard blanket group, 6.1 (5.8 to 6.5) °C in ambulance blanket group and 1.1 (0.7 to 1.6) °C in Ready-Heat II blanket group. In this study, using a torso model based on two 5 L dialysate bags we found the Ready-Heat II heating blanket and Blizzard blanket were associated with lower rates of heat loss after 60 min environmental exposure than the other devices tested. Published by the BMJ Publishing Group Limited. For permission to use (where not already granted under a licence) please go to http://www.bmj.com/company/products-services/rights-and-licensing/

A passively-safe fusion reactor blanket with helium coolant and steel structure

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

Crosswait, Kenneth Mitchell

1994-04-01

Helium is attractive for use as a fusion blanket coolant for a number of reasons. It is neutronically and chemically inert, nonmagnetic, and will not change phase during any off-normal or accident condition. A significant disadvantage of helium, however, is its low density and volumetric heat capacity. This disadvantage manifests itself most clearly during undercooling accident conditions such as a loss of coolant accident (LOCA) or a loss of flow accident (LOFA). This thesis describes a new helium-cooled tritium breeding blanket concept which performs significantly better during such accidents than current designs. The proposed blanket uses reduced-activation ferritic steel asmore » a structural material and is designed for neutron wall loads exceeding 4 MW/m{sup 2}. The proposed geometry is based on the nested-shell concept developed by Wong, but some novel features are used to reduce the severity of the first wall temperature excursion. These features include the following: (1) A ``beryllium-joint`` concept is introduced, which allows solid beryllium slabs to be used as a thermal conduction path from the first wall to the cooler portions of the blanket. The joint concept allows for significant swelling of the beryllium (10 percent or more) without developing large stresses in the blanket structure. (2) Natural circulation of the coolant in the water-cooled shield is used to maintain shield temperatures below 100 degrees C, thus maintaining a heat sink close to the blanket during the accident. This ensures the long-term passive safety of the blanket.« less

Security Blanket or Mother: Which Benefits Linus during Pediatric Examinations?

ERIC Educational Resources Information Center

Ybarra, Gabriel; Passman, Richard H.; Eisenberg, Carl S. L.

This study compared the degree to which young children were placated during a standard medical evaluation by the presence of their mother, blanket, mother plus blanket, or no supportive agent. Participating were 64 three-year-olds who underwent 4 routine medical procedures. Children were rated by their mothers as attached or nonattached to…

18 CFR 284.224 - Certain transportation and sales by local distribution companies.

Code of Federal Regulations, 2014 CFR

2014-04-01

... NATURAL GAS POLICY ACT OF 1978 AND RELATED AUTHORITIES Blanket Certificates Authorizing Certain... to the jurisdiction of the Commission, by reason of section 1(c) of the Natural Gas Act. (b) Blanket... apply for a blanket certificate under this section. (2) Upon application for a certificate under this...

18 CFR 284.224 - Certain transportation and sales by local distribution companies.

Code of Federal Regulations, 2011 CFR

2011-04-01

... NATURAL GAS POLICY ACT OF 1978 AND RELATED AUTHORITIES Blanket Certificates Authorizing Certain... to the jurisdiction of the Commission, by reason of section 1(c) of the Natural Gas Act. (b) Blanket... apply for a blanket certificate under this section. (2) Upon application for a certificate under this...

18 CFR 284.224 - Certain transportation and sales by local distribution companies.

Code of Federal Regulations, 2013 CFR

2013-04-01

... NATURAL GAS POLICY ACT OF 1978 AND RELATED AUTHORITIES Blanket Certificates Authorizing Certain... to the jurisdiction of the Commission, by reason of section 1(c) of the Natural Gas Act. (b) Blanket... apply for a blanket certificate under this section. (2) Upon application for a certificate under this...

18 CFR 284.224 - Certain transportation and sales by local distribution companies.

Code of Federal Regulations, 2012 CFR

2012-04-01

... NATURAL GAS POLICY ACT OF 1978 AND RELATED AUTHORITIES Blanket Certificates Authorizing Certain... to the jurisdiction of the Commission, by reason of section 1(c) of the Natural Gas Act. (b) Blanket... apply for a blanket certificate under this section. (2) Upon application for a certificate under this...

76 FR 13612 - Freebird Gas Storage, LLC; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-14

... Storage, LLC; Notice of Request Under Blanket Authorization Take notice that on March 1, 2011, Freebird Gas Storage, LLC (Freebird) filed a Prior Notice Request pursuant to sections 157.205 and 157.208 of... blanket certificate for authorization to increase the storage capacity and deliverability at its East...

75 FR 19954 - Cheniere Marketing, LLC; Application for Blanket Authorization To Export Liquefied Natural Gas

Federal Register 2010, 2011, 2012, 2013, 2014

2010-04-16

... DEPARTMENT OF ENERGY [FE Docket No. 10-31-LNG] Cheniere Marketing, LLC; Application for Blanket... receipt of an application, filed on March 23, 2010, by Cheniere Marketing, LLC (CMI), requesting blanket... amended to reflect a name change from Cheniere Marketing, Inc to Cheniere Marketing, LLC.\\1\\ \\1\\ Cheniere...

Performance and economics analysis of several laser fusion breeder fueled electricity generation systems

NASA Astrophysics Data System (ADS)

Berwald, D. H.; Maniscalco, J. A.

1981-01-01

The paper evaluates the potential of several future electricity generating systems composed of laser fusion-driven breeder reactors that provide fissile fuel for current technology light water fission power reactors (LWRs). The performance and economic feasibility of four fusion breeder blanket technologies for laser fusion drivers, namely uranium fast fission (UFF) blankets, uranium-thorium fast fission (UTFF) blankets, thorium fast fission (TFF) blankets and thorium-suppressed fission (TSF) blankets, are considered, including design and costs of two kinds, fixed (indirect) costs associated with plant capital and variable (direct) costs associated with fuel processing and operation and maintenance. Results indicate that the UTFF and TFF systems produce electricity most inexpensively and that any of the four breeder blanket concepts, including the TSF and UFF systems, can produce electricity for about 25 to 33% above the cost of electricity produced by a new LWR operating on the current once-through cycle. It is suggested that fusion breeders could supply most or all of our fissile fuel makeup requirements within about 20 years after commercial introduction.

Liquid surfaces for fusion plasma facing components—A critical review. Part I: Physics and PSI

DOE PAGES

Nygren, R. E.; Tabares, F. L.

2016-12-01

This review of the potential of robust plasma facing components (PFCs) with liquid surfaces for applications in future D/T fusion device summarizes the critical issues for liquid surfaces and research being done worldwide in confinement facilities, and supporting R&D in plasma surface interactions. In the paper are a set of questions and related criteria by which we will judge the progress and readiness of liquid surface PFCs. Part-II (separate paper) will cover R&D on the technology-oriented aspects of liquid surfaces including the liquid surfaces as integrated first walls in tritium breeding blankets, tritium retention and recovery, and safety.

Scanning Tunneling Microscopy analysis of space-exposed polymer films

NASA Technical Reports Server (NTRS)

Kalil, Carol R.; Young, Philip R.

1993-01-01

The characterization of the surface of selected space-exposed polymer films by Scanning Tunneling Microscopy (STM) is reported. Principles of STM, an emerging new technique for materials analysis, are reviewed. The analysis of several films which received up to 5.8 years of low Earth orbital (LEO) exposure onboard the NASA Long Duration Exposure Facility (LDEF) is discussed. Specimens included FEP Teflon thermal blanket material, Kapton film, and several experimental polymer films. Ultraviolet and atomic oxygen-induced crazing and erosion are described. The intent of this paper is to demonstrate how STM is enhancing the understanding of LEO space environmental effects on polymer films.

KSC-04PD-0431

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers remove the protective cover from NASAs MESSENGER spacecraft. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-04PD-0442

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. At the Astrotech Space Operations processing facilities, workers check the placement of NASAs MESSENGER spacecraft on a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-04PD-0432

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers remove the protective cover from NASAs MESSENGER spacecraft. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-04PD-0443

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. At the Astrotech Space Operations processing facilities, workers check the placement of NASAs MESSENGER spacecraft on a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-04PD-0429

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. At the Astrotech Space Operations processing facilities near KSC, workers move NASAs MESSENGER spacecraft into a high bay clean room. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-2012-3431

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, technicians install protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-2012-3438

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, technicians install protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

Atomic Oxygen Cleaning of Unpainted Plaster Sculptures

NASA Technical Reports Server (NTRS)

Banks, Bruce A.; Miller, Sharon K.

2017-01-01

Atomic oxygen erosion of polymers has been found to be a threat to spacecraft in low Earth orbit. As a result ground facilities have been developed to identify coatings to protect polymers such as used for solar array blankets. As a result of extensive laboratory testing, it was discovered that soot and other organic contamination on paintings could be readily removed by atomic oxygen interactions with minimal damage to the artwork. No method, other than dusting, has been found to be effective in the cleaning of unpainted plaster sculptures This presentation discusses the atomic oxygen interaction processes and how effective they are for cleaning soot damaged unpainted plaster sculptures.

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

L. Zakharov, J. Li and Y. Wu

The project of ASIPP (with PPPL participation), called FFRF, (R/a=4/1 m/m, Ipl=5 MA, Btor=4-6 T, PDT=50-100 MW, Pfission=80-4000 MW, 1 m thick blanket) is outlined. FFRF stands for the Fusion-Fission Research Facility with a unique fusion mission and a pioneering mission of merging fusion and fission for accumulation of design, experimental, and operational data for future hybrid applications. The design of FFRF will use as much as possible the EAST and ITER design experience. On the other hand, FFRF strongly relies on new, Lithium Wall Fusion plasma regimes, the development of which has already started in the US and China.

Hubble Space Telescope Thermal Blanket Repair Design and Implementation

NASA Technical Reports Server (NTRS)

Ousley, Wes; Skladany, Joseph; Dell, Lawrence

2000-01-01

Substantial damage to the outer layer of Hubble Space Telescope (HST) thermal blankets was observed during the February 1997 servicing mission. After six years in LEO, many areas of the aluminized Teflon(R) outer blanket layer had significant cracks, and some material was peeled away to expose inner layers to solar flux. After the mission, the failure mechanism was determined, and repair materials and priorities were selected for follow-on missions. This paper focuses on the thermal, mechanical, and EVA design requirements for the blanket repair, the creative solutions developed for these unique problems, hardware development, and testing.

Beryllium R&D for blanket application

NASA Astrophysics Data System (ADS)

Donne, M. Dalle; Longhurst, G. R.; Kawamura, H.; Scaffidi-Argentina, F.

1998-10-01

The paper describes the main problems and the R&D for the beryllium to be used as neutron multiplier in blankets. As the four ITER partners propose to use beryllium in the form of pebbles for their DEMO relevant blankets (only the Russians consider the porous beryllium option as an alternative) and the ITER breeding blanket will use beryllium pebbles as well, the paper is mainly based on beryllium pebbles. Also the work on the chemical reactivity of fully dense and porous beryllium in contact with water steam is described, due to the safety importance of this point.

Disinfection of woollen blankets in steam at subatmospheric pressure

PubMed Central

Alder, V. G.; Gillespie, W. A.

1961-01-01

Blankets may be disinfected in steam at subatmospheric pressures by temperatures below boiling point inside a suitably adapted autoclave chamber. The chamber and its contents are thoroughly evacuated of air so as to allow rapid heat penetration, and steam is admitted to a pressure of 10 in. Hg below atmospheric pressure, which corresponds to a temperature of 89°C. Woollen blankets treated 50 times by this process were undamaged. Vegetative organisms were destroyed but not spores. The method is suitable for large-scale disinfection of blankets and for disinfecting various other articles which would be damaged at higher temperatures. PMID:13860203

Personnel dose reduction in 90Y microspheres liver-directed radioembolization: from interventional radiology suite to patient ward

PubMed Central

Wong, K K; Tso, W K; Lee, Victor; Luk, M Y; Tong, C C; Chu, Ferdinand

2017-01-01

Objective: To describe a method to reduce the external radiation exposure emitted from the patient after liver-directed radioembolization using 90Y glass microspheres, to quantitatively estimate the occupational dose of medical personnel providing patient care to the patient radioembolized with the use of the method and to discuss radiation exposure to patients who are adjacent if the patient radioembolized needs hospitalization. Methods: A lead-lined blanket of lead equivalence of 0.5 mm was used to cover the patient abdomen immediately after the 90Y radioembolization procedure, in order to reduce the radiation emitted from the patient. The interventional radiologist used a rod-type puncture site compressor for haemostasis to avoid direct contact with possible residual radioactivity at the puncture site. Dose rates were measured at the interventional radiologist chest and hand positions during puncture site pressing for haemostasis with and without the use of the blanket. The measurement results were applied to estimate the occupational dose of colleagues performing patient care to the patient radioembolized. The exposure to patients adjacent in the ward was estimated if the patient radioembolized was hospitalized. Results: The radiation exposures measured at the radiologist chest and hand positions have been significantly reduced with the lead-lined blanket in place. The radiologist, performing puncture site pressing at the end of radioembolization procedure, would receive an average hand dose of 1.95 μSv and body dose under his own lead apron of 0.30 μSv for an average 90Y microsphere radioactivity of 2.54 GBq. Other medical personnel, nurses and porters, would receive occupational doses corresponding to an hour of background radiation. If the patient radioembolized using 90Y needs hospitalization in a common ward, using the lead-lined blanket to cover the abdomen of the patient and keeping a distance of 2 m from the patient who is adjacent would reduce the exposure by 0.42% of dose limit for the general public. Conclusion: By placing a lead-lined blanket on the patient abdominal region after 90Y radioembolization, hospital staff receive minimal radiation exposure in order to comply with the radiation protection “as low as reasonably achievable” principle. There will be no increase in radiation level in ward if the patient radioembolized using 90Y needs to be hospitalized. Therefore, the patient radioembolized can be accommodated alternatively at a corner bed of a common ward if an isolation room with private toilet facility is not available. Advances in knowledge: To reduce exposure to personnel providing patient care to patients radioembolized using 90Y. PMID:27993095

Design, Manufacture, and Experimental Serviceability Validation of ITER Blanket Components

NASA Astrophysics Data System (ADS)

Leshukov, A. Yu.; Strebkov, Yu. S.; Sviridenko, M. N.; Safronov, V. M.; Putrik, A. B.

2017-12-01

In 2014, the Russian Federation and the ITER International Organization signed two Procurement Arrangements (PAs) for ITER blanket components: 1.6.P1ARF.01 "Blanket First Wall" of February 14, 2014, and 1.6.P3.RF.01 "Blanket Module Connections" of December 19, 2014. The first PA stipulates development, manufacture, testing, and delivery to the ITER site of 179 Enhanced Heat Flux (EHF) First Wall (FW) Panels intended for withstanding the heat flux from the plasma up to 4.7MW/m2. Two Russian institutions, NIIEFA (Efremov Institute) and NIKIET, are responsible for the implementation of this PA. NIIEFA manufactures plasma-facing components (PFCs) of the EHF FW panels and performs the final assembly and testing of the panels, and NIKIET manufactures FW beam structures, load-bearing structures of PFCs, and all elements of the panel attachment system. As for the second PA, NIKIET is the sole official supplier of flexible blanket supports, electrical insulation key pads (EIKPs), and blanket module/vacuum vessel electrical connectors. Joint activities of NIKIET and NIIEFA for implementing PA 1.6.P1ARF.01 are briefly described, and information on implementation of PA 1.6.P3.RF.01 is given. Results of the engineering design and research efforts in the scope of the above PAs in 2015-2016 are reported, and results of developing the technology for manufacturing ITER blanket components are presented.

75 FR 13755 - Freeport LNG Development, L.P.; Application To Amend Blanket Authorization To Export Liquefied...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-03-23

... Amend Blanket Authorization To Export Liquefied Natural Gas AGENCY: Office of Fossil Energy, DOE. ACTION: Notice of Application to Amend Blanket Authorization. SUMMARY: The Office of Fossil Energy (FE) of the... Oil and Gas Global Security and Supply, Office of Fossil Energy, Forrestal Building, Room 3E-042, 1000...

75 FR 59167 - Airworthiness Directives; The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-09-27

... inner wall and insulation blankets). This proposed AD results from reports of heat damage to the inner... insulation blankets and heat transfer through the upper compression pad area and the fireseal bracket support... upper and lower inner wall insulation blankets, measuring the electrical conductivity on the aluminum...

78 FR 4400 - Eni USA Gas Marketing LLC; Application for Blanket Authorization To Export Previously Imported...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-01-22

... DEPARTMENT OF ENERGY [FE Docket No. 12-161-LNG] Eni USA Gas Marketing LLC; Application for Blanket..., by Eni USA Gas Marketing LLC (Eni USA Gas Marketing), requesting blanket authorization to export... U.S. law or policy. Eni USA Gas Marketing is requesting this authorization both on its own behalf...

Testing Seam Concepts for Advanced Multilayer Insulation

NASA Technical Reports Server (NTRS)

Chato, D. J.; Johnson, W. L.; Alberts, Samantha J.

2017-01-01

Multilayer insulation (MLI) is considered the state of the art insulation for cryogenic propellant tanks in the space environment. MLI traditionally consists of multiple layers of metalized films separated by low conductivity spacers. In order to better understand some of the details within MLI design and construction, GRC has been investigating the heat loads caused by multiple types of seams. To date testing has been completed with 20 layer and 50 layer blankets. Although a truly seamless blanket is not practical, a blanket lay-up where each individual layer was overlapped and tapped together was used as a baseline for the other seams tests. Other seams concepts tested included: an overlap where the complete blanket was overlapped on top of itself; a butt joint were the blankets were just trimmed and butted up against each other, and a staggered butt joint where the seam in the out layers is offset from the seam in the inner layers. Measured performance is based on a preliminary analysis of rod calibration tests conducted prior to the start of seams testing. Baseline performance for the 50 layer blanket showed a measured heat load of 0.46 Watts with a degradation to about 0.47 Watts in the seamed blankets. Baseline performance for the 20 layer blanket showed a measured heat load of 0.57 Watts. Heat loads for the seamed tests are still begin analyzed. So far analysis work has suggested the need for corrections due to heat loads from both the heater leads and the instrumentation wires. A careful re-examination of the calibration test results with these factors accounted for is also underway. This presentation will discuss the theory of seams in MLI, our test results to date, and the uncertainties in our measurements.

Multilayer insulation blanket, fabricating apparatus and method

DOEpatents

Gonczy, John D.; Niemann, Ralph C.; Boroski, William N.

1992-01-01

An improved multilayer insulation blanket for insulating cryogenic structures operating at very low temperatures is disclosed. An apparatus and method for fabricating the improved blanket are also disclosed. In the improved blanket, each successive layer of insulating material is greater in length and width than the preceding layer so as to accommodate thermal contraction of the layers closest to the cryogenic structure. The fabricating apparatus has a rotatable cylindrical mandrel having an outer surface of fixed radius that is substantially arcuate, preferably convex, in cross-section. The method of fabricating the improved blanket comprises (a) winding a continuous sheet of thermally reflective material around the circumference of the mandrel to form multiple layers, (b) binding the layers along two lines substantially parallel to the edges of the circumference of the mandrel, (c) cutting the layers along a line parallel to the axle of the mandrel, and (d) removing the bound layers from the mandrel.

Method of fabricating a multilayer insulation blanket

DOEpatents

Gonczy, John D.; Niemann, Ralph C.; Boroski, William N.

1993-01-01

An improved multilayer insulation blanket for insulating cryogenic structures operating at very low temperatures is disclosed. An apparatus and method for fabricating the improved blanket are also disclosed. In the improved blanket, each successive layer of insulating material is greater in length and width than the preceding layer so as to accommodate thermal contraction of the layers closest to the cryogenic structure. The fabricating apparatus has a rotatable cylindrical mandrel having an outer surface of fixed radius that is substantially arcuate, preferably convex, in cross-section. The method of fabricating the improved blanket comprises (a) winding a continuous sheet of thermally reflective material around the circumference of the mandrel to form multiple layers, (b) binding the layers along two lines substantially parallel to the edges of the circumference of the mandrel, (c) cutting the layers along a line parallel to the axle of the mandrel, and (d) removing the bound layers from the mandrel.

Method of fabricating a multilayer insulation blanket

DOEpatents

Gonczy, J.D.; Niemann, R.C.; Boroski, W.N.

1993-07-06

An improved multilayer insulation blanket for insulating cryogenic structures operating at very low temperatures is disclosed. An apparatus and method for fabricating the improved blanket are also disclosed. In the improved blanket, each successive layer of insulating material is greater in length and width than the preceding layer so as to accommodate thermal contraction of the layers closest to the cryogenic structure. The fabricating apparatus has a rotatable cylindrical mandrel having an outer surface of fixed radius that is substantially arcuate, preferably convex, in cross-section. The method of fabricating the improved blanket comprises (a) winding a continuous sheet of thermally reflective material around the circumference of the mandrel to form multiple layers, (b) binding the layers along two lines substantially parallel to the edges of the circumference of the mandrel, (c) cutting the layers along a line parallel to the axle of the mandrel, and (d) removing the bound layers from the mandrel.

Multilayer insulation blanket, fabricating apparatus and method

DOEpatents

Gonczy, J.D.; Niemann, R.C.; Boroski, W.N.

1992-09-01

An improved multilayer insulation blanket for insulating cryogenic structures operating at very low temperatures is disclosed. An apparatus and method for fabricating the improved blanket are also disclosed. In the improved blanket, each successive layer of insulating material is greater in length and width than the preceding layer so as to accommodate thermal contraction of the layers closest to the cryogenic structure. The fabricating apparatus has a rotatable cylindrical mandrel having an outer surface of fixed radius that is substantially arcuate, preferably convex, in cross-section. The method of fabricating the improved blanket comprises (a) winding a continuous sheet of thermally reflective material around the circumference of the mandrel to form multiple layers, (b) binding the layers along two lines substantially parallel to the edges of the circumference of the mandrel, (c) cutting the layers along a line parallel to the axle of the mandrel, and (d) removing the bound layers from the mandrel. 7 figs.

An Analysis of Ripple and Error Fields Induced by a Blanket in the CFETR

NASA Astrophysics Data System (ADS)

Yu, Guanying; Liu, Xufeng; Liu, Songlin

2016-10-01

The Chinese Fusion Engineering Tokamak Reactor (CFETR) is an important intermediate device between ITER and DEMO. The Water Cooled Ceramic Breeder (WCCB) blanket whose structural material is mainly made of Reduced Activation Ferritic/Martensitic (RAFM) steel, is one of the candidate conceptual blanket design. An analysis of ripple and error field induced by RAFM steel in WCCB is evaluated with the method of static magnetic analysis in the ANSYS code. Significant additional magnetic field is produced by blanket and it leads to an increased ripple field. Maximum ripple along the separatrix line reaches 0.53% which is higher than 0.5% of the acceptable design value. Simultaneously, one blanket module is taken out for heating purpose and the resulting error field is calculated to be seriously against the requirement. supported by National Natural Science Foundation of China (No. 11175207) and the National Magnetic Confinement Fusion Program of China (No. 2013GB108004)

Increase in transmission loss of a double panel system by addition of mass inclusions to a poro-elastic layer: A comparison between theory and experiment

NASA Astrophysics Data System (ADS)

Idrisi, Kamal; Johnson, Marty E.; Toso, Alessandro; Carneal, James P.

2009-06-01

This paper is concerned with the modeling and optimization of heterogeneous (HG) blankets, which are used in this investigation to reduce the sound transmission through double panel systems. HG blankets consist of poro-elastic media with small embedded masses, which act similarly to a distributed mass-spring-damper-system. HG blankets have shown significant potential to reduce low frequency radiated sound from structures, where traditional poro-elastic materials have little effect. A mathematical model of a double panel system with an acoustic cavity and HG blanket was developed using impedance and mobility methods. The predicted responses of the source and the receiving panel due to a point force are validated with experimental measurements. The presented results indicate that proper tuning of the HG blankets can result in broadband noise reduction below 500 Hz with less than 10% added mass.

A preliminary report on the study of the impact sites and particles of the solar maximum satellite thermal blanket

NASA Technical Reports Server (NTRS)

Zook, H. A.

1985-01-01

A preliminary study of the work on examination of the impact pits in, or penetrations through, the thermal blankets of the Solar Maximum Satellite is presented. The three largest pieces of the thermal blanket were optically scanned with a total surface area of about one half square meter. Over 1500 impact sites of all sizes, including 432 impacts larger than 40 microns in diameter, have been documented. Craters larger in diameter than about 100 microns found on the 75 micron thick Kapton first sheet of the main electronics box blanket are actually holes and constitute perforations through the blanket. A summary of the impact pit population that were found is given. The chemical study of these craters is only in the initial stages, with only about 250 chemical spectra of particles observed in or around impact pits or in the debris pattern being recorded.

Behaviour of Li 2ZrO 3 and Li 2TiO 3 pebbles relevant to their utilization as ceramic breeder for the HCPB blanket

NASA Astrophysics Data System (ADS)

Lulewicz, J. D.; Roux, N.; Piazza, G.; Reimann, J.; van der Laan, J.

2000-12-01

Li 2ZrO 3 and Li 2TiO 3 pebbles are being investigated at Commissariat à l'Energie Atomique as candidate alternative ceramics for the European helium-cooled pebble bed (HCPB) blanket. The pebbles are fabricated using the extrusion-spheronization-sintering process and are optimized regarding composition, geometrical characteristics, microstructural characteristics, and material purity. Tests were designed and are being performed with other organizations so as to check the functional performance of the pebbles and pebble beds with respect to the HCPB blanket requirements, and, finally, to make the selection of the most appropriate ceramic for the HCPB blanket. Tests include high temperature long-term annealing, thermal shock, thermal cycling, thermal mechanical behaviour of pebble beds, thermal conductivity of pebble beds, and tritium extraction. Current results indicate the attractiveness of these ceramics pebbles for the HCPB blanket.

Investigation of heat transfer in liquid-metal flows under fusion-reactor conditions

NASA Astrophysics Data System (ADS)

Poddubnyi, I. I.; Pyatnitskaya, N. Yu.; Razuvanov, N. G.; Sviridov, V. G.; Sviridov, E. V.; Leshukov, A. Yu.; Aleskovskiy, K. V.; Obukhov, D. M.

2016-12-01

The effect discovered in studying a downward liquid-metal flow in vertical pipe and in a channel of rectangular cross section in, respectively, a transverse and a coplanar magnetic field is analyzed. In test blanket modules (TBM), which are prototypes of a blanket for a demonstration fusion reactor (DEMO) and which are intended for experimental investigations at the International Thermonuclear Experimental Reactor (ITER), liquid metals are assumed to fulfil simultaneously the functions of (i) a tritium breeder, (ii) a coolant, and (iii) neutron moderator and multiplier. This approach to testing experimentally design solutions is motivated by plans to employ, in the majority of the currently developed DEMO blanket projects, liquid metals pumped through pipes and/or rectangular channels in a transvers magnetic field. At the present time, experiments that would directly simulate liquid-metal flows under conditions of ITER TBM and/or DEMO blanket operation (irradiation with thermonuclear neutrons, a cyclic temperature regime, and a magnetic-field strength of about 4 to 10 T) are not implementable for want of equipment that could reproduce simultaneously the aforementioned effects exerted by thermonuclear plasmas. This is the reason why use is made of an iterative approach to experimentally estimating the performance of design solutions for liquid-metal channels via simulating one or simultaneously two of the aforementioned factors. Therefore, the investigations reported in the present article are of considerable topical interest. The respective experiments were performed on the basis of the mercury magneto hydrodynamic (MHD) loop that is included in the structure of the MPEI—JIHT MHD experimental facility. Temperature fields were measured under conditions of two- and one-sided heating, and data on averaged-temperature fields, distributions of the wall temperature, and statistical fluctuation features were obtained. A substantial effect of counter thermo gravitational convection (TGC) on averaged and fluctuating quantities were found. The development of TGC in the presence of a magnetic field leads to the appearance of low-frequency fluctuations whose anomalously high intensity exceeds severalfold the level of turbulence fluctuations. This effect manifest itself over a broad region of regime parameters. It was confirmed that low-energy fluctuations penetrate readily through the wall; therefore, it is necessary to study this effect further—in particular, from the point of view of the fatigue strength of the walls of liquid-metal channels.

Investigation of heat transfer in liquid-metal flows under fusion-reactor conditions

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

Poddubnyi, I. I., E-mail: poddubnyyii@nikiet.ru; Pyatnitskaya, N. Yu.; Razuvanov, N. G.

2016-12-15

The effect discovered in studying a downward liquid-metal flow in vertical pipe and in a channel of rectangular cross section in, respectively, a transverse and a coplanar magnetic field is analyzed. In test blanket modules (TBM), which are prototypes of a blanket for a demonstration fusion reactor (DEMO) and which are intended for experimental investigations at the International Thermonuclear Experimental Reactor (ITER), liquid metals are assumed to fulfil simultaneously the functions of (i) a tritium breeder, (ii) a coolant, and (iii) neutron moderator and multiplier. This approach to testing experimentally design solutions is motivated by plans to employ, in themore » majority of the currently developed DEMO blanket projects, liquid metals pumped through pipes and/or rectangular channels in a transvers magnetic field. At the present time, experiments that would directly simulate liquid-metal flows under conditions of ITER TBM and/or DEMO blanket operation (irradiation with thermonuclear neutrons, a cyclic temperature regime, and a magnetic-field strength of about 4 to 10 T) are not implementable for want of equipment that could reproduce simultaneously the aforementioned effects exerted by thermonuclear plasmas. This is the reason why use is made of an iterative approach to experimentally estimating the performance of design solutions for liquid-metal channels via simulating one or simultaneously two of the aforementioned factors. Therefore, the investigations reported in the present article are of considerable topical interest. The respective experiments were performed on the basis of the mercury magneto hydrodynamic (MHD) loop that is included in the structure of the MPEI—JIHT MHD experimental facility. Temperature fields were measured under conditions of two- and one-sided heating, and data on averaged-temperature fields, distributions of the wall temperature, and statistical fluctuation features were obtained. A substantial effect of counter thermo gravitational convection (TGC) on averaged and fluctuating quantities were found. The development of TGC in the presence of a magnetic field leads to the appearance of low-frequency fluctuations whose anomalously high intensity exceeds severalfold the level of turbulence fluctuations. This effect manifest itself over a broad region of regime parameters. It was confirmed that low-energy fluctuations penetrate readily through the wall; therefore, it is necessary to study this effect further—in particular, from the point of view of the fatigue strength of the walls of liquid-metal channels.« less

Neutronics and activation analysis of lithium-based ternary alloys in IFE blankets

DOE PAGES

Jolodosky, Alejandra; Kramer, Kevin; Meier, Wayne; ...

2016-04-09

Here we report that an attractive feature of using liquid lithium as the breeder and coolant in fusion blankets is that it has very high tritium solubility and results in very low levels of tritium permeation throughout the facility infrastructure. However, lithium metal vigorously reacts with air and water and presents plant safety concerns. The Lawrence Livermore National Laboratory is carrying an effort to develop a lithium-based alloy that maintains the beneficial properties of lithium (e.g. high tritium breeding and solubility) and at the same time reduces overall flammability concerns. This study evaluates the neutronics performance of lithium-based alloys inmore » the blanket of an inertial fusion energy chamber in order to inform such development. 3-D Monte Carlo calculations were performed to evaluate two main neutronics performance parameters for the blanket: tritium breeding ratio (TBR), and the fusion energy multiplication factor (EMF). It was found that elements that exhibit low absorption cross sections and higher q-values such as lead, tin, and strontium, perform well with those that have high neutron multiplication such as lead and bismuth. These elements meet TBR constrains ranging from 1.02 to 1.1. However, most alloys do not reach EMFs greater than 1.15. Additionally, it was found that enriching lithium significantly increases the TBR and decreases the minimum lithium concentration by more than 60%. The amount of enrichment depends on how much total lithium is in the alloy to begin with. Alloys that performed well in the TBR and EMF calculations were considered for activation analysis. Activation simulations were executed with 50 years of irradiation and 300 years of cooling. It was discovered that bismuth is a poor choice due to achieving the highest decay heat, contact dose rates, and accident doses. In addition, it does not meet the waste disposal ratings (WDR). Some of the activation results for alloys with tin, zinc, and gallium were in the higher end and should be considered secondary to elements such as strontium and barium that had overall better results. The results of this study along with other considerations such as thermodynamics, and chemical reactivity will help down select a preferred lithium ternary alloy.« less

Air data position-error calibration using state reconstruction techniques

NASA Technical Reports Server (NTRS)

Whitmore, S. A.; Larson, T. J.; Ehernberger, L. J.

1984-01-01

During the highly maneuverable aircraft technology (HiMAT) flight test program recently completed at NASA Ames Research Center's Dryden Flight Research Facility, numerous problems were experienced in airspeed calibration. This necessitated the use of state reconstruction techniques to arrive at a position-error calibration. For the HiMAT aircraft, most of the calibration effort was expended on flights in which the air data pressure transducers were not performing accurately. Following discovery of this problem, the air data transducers of both aircraft were wrapped in heater blankets to correct the problem. Additional calibration flights were performed, and from the resulting data a satisfactory position-error calibration was obtained. This calibration and data obtained before installation of the heater blankets were used to develop an alternate calibration method. The alternate approach took advantage of high-quality inertial data that was readily available. A linearized Kalman filter (LKF) was used to reconstruct the aircraft's wind-relative trajectory; the trajectory was then used to separate transducer measurement errors from the aircraft position error. This calibration method is accurate and inexpensive. The LKF technique has an inherent advantage of requiring that no flight maneuvers be specially designed for airspeed calibrations. It is of particular use when the measurements of the wind-relative quantities are suspected to have transducer-related errors.

Deep Space 1 is prepared for transport to launch pad

NASA Technical Reports Server (NTRS)

1998-01-01

In the Defense Satellite Communications Systems Processing Facility (DPF), Cape Canaveral Air Station (CCAS), after covering the lower portion of Deep Space 1, workers adjust the anti-static blanket covering the upper portion. The blanket will protect the spacecraft during transport to the launch pad. Deep Space 1 is the first flight in NASA's New Millennium Program, and is designed to validate 12 new technologies for scientific space missions of the next century, including the engine. Propelled by the gas xenon, the engine is being flight-tested for future deep space and Earth-orbiting missions. Deceptively powerful, the ion drive emits only an eerie blue glow as ionized atoms of xenon are pushed out of the engine. While slow to pick up speed, over the long haul it can deliver 10 times as much thrust per pound of fuel as liquid or solid fuel rockets. Other onboard experiments include software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but will also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, CCAS.

KSC-98pc1316

NASA Image and Video Library

1998-10-10

KENNEDY SPACE CENTER, FLA. -- In the Defense Satellite Communications Systems Processing Facility (DPF), Cape Canaveral Air Station (CCAS), after covering the lower portion of Deep Space 1, workers adjust the anti-static blanket covering the upper portion. The blanket will protect the spacecraft during transport to the launch pad. Deep Space 1 is the first flight in NASA's New Millennium Program, and is designed to validate 12 new technologies for scientific space missions of the next century, including the engine. Propelled by the gas xenon, the engine is being flight-tested for future deep space and Earth-orbiting missions. Deceptively powerful, the ion drive emits only an eerie blue glow as ionized atoms of xenon are pushed out of the engine. While slow to pick up speed, over the long haul it can deliver 10 times as much thrust per pound of fuel as liquid or solid fuel rockets. Other onboard experiments include software that tracks celestial bodies so the spacecraft can make its own navigation decisions without the intervention of ground controllers. Deep Space 1 will complete most of its mission objectives within the first two months, but will also do a flyby of a near-Earth asteroid, 1992 KD, in July 1999. Deep Space 1 will be launched aboard a Boeing Delta 7326 rocket from Launch Pad 17A, CCAS

Retrieval of Mir Solar Array

NASA Technical Reports Server (NTRS)

Rutledge, Sharon K.; deGroh, Kim K.

1999-01-01

A Russian solar array panel removed in November 1997 from the non-articulating photovoltaic array on the Mir core module was returned to Earth on STS-89 in January 1998. The panel had been exposed to low Earth orbit (LEO) for 10 years prior to retrieval. The retrieval provided a unique opportunity to study the effects of the LEO environment on a functional solar array. To take advantage of this opportunity, a team composed of members from RSC-Energia (Russia), the Boeing Company, and the following NASA Centers--Johnson Space Center, Kennedy Space Center, Langley Research Center, Marshall Space Flight Center, and Lewis Research Center--was put together to analyze the array. After post-retrieval inspections at the Spacehab Facility at Kennedy in Florida, the array was shipped to Lewis in Cleveland for electrical performance tests, closeup photodocumentation, and removal of selected solar cells and blanket material. With approval from RSC-Energia, five cell pairs and their accompanying blanket and mesh material, and samples of painted handrail materials were selected for removal on the basis of their ability to provide degradation information. Sites were selected that provided different sizes and shapes of micrometeoroid impacts and different levels of surface contamination. These materials were then distributed among the team for round robin testing.

An investigation of the degradation of Fluorinated Ethylene Propylene (FEP) copolymer thermal blanketing materials aboard LDEF in the laboratory

NASA Technical Reports Server (NTRS)

Stiegman, A. E.; Brinza, David E.; Anderson, Mark S.; Minton, Timothy K.; Laue, Eric G.; Liang, Ranty H.

1991-01-01

Samples of fluorinated ethylene propylene copolymer thermal blanketing material, recovered from the Long Duration Exposure Facility (LDEF), were investigated to determine the nature and the extent of degradation due to exposure to the low-Earth-orbit environment. Samples recovered from the ram-facing direction of LDEF, which received vacuum-ultraviolet (VUV) radiation and atomic-oxygen impingement, and samples from the trailing edge, which received almost exclusively VUV exposure, were investigated by scanning electron microscopy and atomic force microscopy. The most significant result of this investigation was found on samples that received only VUV exposure. These samples possessed a hard, embrittled surface layer that was absent from the atomic-oxygen exposed sample and from unexposed control samples. This surface layer is believed to be responsible for the 'synergistic' effect between VUV and atomic oxygen. Overall, the investigation revealed dramatically different morphologies for the two samples. The sample receiving both atomic-oxygen and VUV exposure was deeply eroded and had a characteristic 'rolling' surface morphology, while the sample that received only VUV exposure showed mild erosion and a surface morphology characterized by sharp high-frequency peaks. The morphologies observed in the LDEF samples, including the embrittled surface layer, were successfully duplicated in the laboratory.

Demonstration Tokamak Hybrid Reactor (DTHR) blanket design study, December 1978

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

Not Available

1978-01-01

This work represents only the second iteration of the conceptual design of a DTHR blanket; consequently, a number of issues important to a detailed blanket design have not yet been evaluated. The most critical issues identified are those of two-phase flow maldistribution, flow instabilities, flow stratification for horizontal radial inflow of boiling water, fuel rod vibrations, corrosion of clad and structural materials by high quality steam, fretting and cyclic loads. Approaches to minimizing these problems are discussed and experimental testing with flow mock-ups is recommended. These implications on a commercial blanket design are discussed and critical data needs are identified.

Preliminary Design of a Helium-Cooled Ceramic Breeder Blanket for CFETR Based on the BIT Concept

NASA Astrophysics Data System (ADS)

Ma, Xuebin; Liu, Songlin; Li, Jia; Pu, Yong; Chen, Xiangcun

2014-04-01

CFETR is the “ITER-like” China fusion engineering test reactor. The design of the breeding blanket is one of the key issues in achieving the required tritium breeding radio for the self-sufficiency of tritium as a fuel. As one option, a BIT (breeder insider tube) type helium cooled ceramic breeder blanket (HCCB) was designed. This paper presents the design of the BIT—HCCB blanket configuration inside a reactor and its structure, along with neutronics, thermo-hydraulics and thermal stress analyses. Such preliminary performance analyses indicate that the design satisfies the requirements and the material allowable limits.

Microvibration and Centre-of-Gravity Shift Measurements on Thermally Stressed Thermal-Control Blankets

NASA Astrophysics Data System (ADS)

Magg, Manfred; Grillenbeck, Anton, , Dr.

2004-08-01

Several samples of thermal control blankets were subjected to transient thermal loads in a thermal vacuum chamber in order to study their ability to excite micro- vibrations on a carrier structure and to cause tiny centre- of-gravity shifts. The reason for this investigation was driven by the GOCE project in order to minimize micro- vibrations on-board of the spacecraft while on-orbit. The objectives of this investigation were to better understand the mechanism which may produce micro- vibrations induced by the thermal control blankets, and to identify thermal control blanket lay-ups with minimum micro-vibration activity.

Improving proliferation resistance of high breeding gain generation 4 reactors using blankets composed of light water reactor waste

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

Hellesen, C.; Grape, S.; Haakanson, A.

2013-07-01

Fertile blankets can be used in fast reactors to enhance the breeding gain as well as the passive safety characteristics. However, such blankets typically result in the production of weapons grade plutonium. For this reason they are often excluded from Generation IV reactor designs. In this paper we demonstrate that using blankets manufactured directly from spent light water (LWR) reactor fuel it is possible to produce a plutonium product with non-proliferation characteristics on a par with spent LWR fuel of 30-50 MWd/kg burnup. The beneficial breeding and safety characteristics are retained. (authors)

Comparison of two passive warming devices for prevention of perioperative hypothermia in dogs.

PubMed

Potter, J; Murrell, J; MacFarlane, P

2015-09-01

To compare effects of two passive warming methods combined with a resistive heating mat on perioperative hypothermia in dogs. Fifty-two dogs were enrolled and randomly allocated to receive a reflective blanket (Blizzard Blanket) or a fabric blanket (VetBed). In addition, in the operating room all dogs were placed onto a table with a resistive heating mat covered with a fabric blanket. Rectal temperature measurements were taken at defined points. Statistical analysis was performed comparing all Blizzard Blanket-treated to all VetBed-treated dogs, and VetBed versus Blizzard Blanket dogs within spay and castrate groups, spay versus castrate groups and within groups less than 10 kg or more than 10 kg bodyweight. Data from 39 dogs were used for analysis. All dogs showed a reduction in perioperative rectal temperature. There were no detected statistical differences between treatments or between the different groups. This study supports previous data on prevalence of hypothermia during surgery. The combination of active and passive warming methods used in this study prevented the development of severe hypothermia, but there were no differences between treatment groups. © 2015 British Small Animal Veterinary Association.

KSC-04pd1849

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - Martin Wilson (far left), manager of Thermal Protection System (TPS) operations for United Space Alliance (USA), leads NASA Administrator Sean O’Keefe (second from left) on a tour of the hurricane-ravaged Thermal Protection System Facility. The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof in the storm, which blew across Central Florida Sept. 4-5. Undamaged equipment was removed from the TPSF and stored in the RLV hangar. O’Keefe and NASA Associate Administrator of Space Operations Mission Directorate William Readdy are visiting KSC to survey the damage sustained by KSC facilities from the hurricane. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters - Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

KSC-04pd1850

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - Martin Wilson (left, in foreground), manager of Thermal Protection System (TPS) operations for United Space Alliance (USA), gives a tour of the hurricane-ravaged Thermal Protection System Facility to (from center) NASA Associate Administrator of Space Operations Mission Directorate William Readdy, NASA Administrator Sean O’Keefe, Center Director James Kennedy and Director of Shuttle Processing Michael E. Wetmore. The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof during Hurricane Frances, which blew across Central Florida Sept. 4-5. O’Keefe and Readdy are visiting KSC to survey the damage sustained by KSC facilities from the hurricane. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters - Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

KSC-04pd1845

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - - United Space Alliance technician Shelly Kipp (right) shows some of the material salvaged from the storm-ravaged Thermal Protection System Facility (TPSF) to NASA Administrator Sean O’Keefe (left). Martin Wilson (center), manager of TPS operations for USA, looks on. The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof during Hurricane Frances, which blew across Central Florida Sept. 4-5. O’Keefe and NASA Associate Administrator of Space Operations Mission Directorate William Readdy are visiting KSC to survey the damage sustained by KSC facilities from the hurricane. Undamaged equipment was removed from the TPSF and stored in the RLV hangar. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters -- Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

Viable Circumstances for Financial Negotiations in Pakistan Contracting Process

DTIC Science & Technology

2015-06-01

Submission BIW Bath Iron Works BPA Blanket Purchase Agreement CERP Center for Economic Research in Pakistan CICA Competition in Contracting Act CJCS...IDIQ contracts, blanket purchase agreements ( BPAs ), and contractors team arrangements (CTAs) by fulfilling all pre-requisites of government...wide commercial purchase card (FAR 13.301) 2. Purchase orders (FAR 13.302) 3. Blanket purchase agreements ( BPAs ; FAR13.303) 4. Imprest fund and

Neutron economic reactivity control system for light water reactors

DOEpatents

Luce, Robert G.; McCoy, Daniel F.; Merriman, Floyd C.; Gregurech, Steve

1989-01-01

A neutron reactivity control system for a LWBR incorporating a stationary seed-blanket core arrangement. The core arrangement includes a plurality of contiguous hexagonal shaped regions. Each region has a central and a peripheral blanket area juxapositioned an annular seed area. The blanket areas contain thoria fuel rods while the annular seed area includes seed fuel rods and movable thoria shim control rods.

Applications of the Aqueous Self-Cooled Blanket concept

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

Steiner, D.; Embrechts, M.J.; Varsamis, G.

1986-11-01

In this paper a novel water-cooled blanket concept is examined. This concept, designated the Aqueous Self-Cooled Blanket (ASCB), employs water with small amounts of dissolved fertile compounds as both the coolant and the breeding medium. The ASCB concept is reviewed and its application in three different contexts is examined: (1) power reactors; (2) near-term devices such as NET; and (3) fusion-fission hybrids.

32 CFR Appendix C to Part 310 - DoD Blanket Routine Uses

Code of Federal Regulations, 2010 CFR

2010-07-01

... 32 National Defense 2 2010-07-01 2010-07-01 false DoD Blanket Routine Uses C Appendix C to Part...) PRIVACY PROGRAM DOD PRIVACY PROGRAM Pt. 310, App. C Appendix C to Part 310—DoD Blanket Routine Uses (See paragraph (c) of § 310.22 of subpart E) A. Routine Use—Law Enforcement If a system of records maintained by...

Predicted and observed directional dependence of meteoroid/debris impacts on LDEF thermal blankets

NASA Technical Reports Server (NTRS)

Drolshagen, Gerhard

1993-01-01

The number of impacts from meteoroids and space debris particles to the various LDEF rows is calculated using ESABASE/DEBRIS, a 3-D numerical analysis tool. It is based on recent reference environment flux models and includes geometrical and directional effects. A comparison of model predictions and actual observations is made for penetrations of the thermal blankets which covered the UHCR experiment. The thermal blankets were located on all LDEF rows, except 3, 9, and 12. Because of their uniform composition and thickness, these blankets allow a direct analysis of the directional dependence of impacts and provide a test case for the latest meteoroid and debris flux models.

An active target for the accelerator-based transmutation system

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

Grebyonkin, K.F.

1995-10-01

Consideration is given to the possibility of radical reduction in power requirements to the proton accelerator of the electronuclear reactor due to neutron multiplication both in the blanket and the target of an active material. The target is supposed to have the fast-neutron spectrum, and the blanket-the thermal one. The blanket and the target are separated by the thermal neutrons absorber, which is responsible for the neutron decoupling of the active target and blanket. Also made are preliminary estimations which illustrate that the realization of the idea under consideration can lead to significant reduction in power requirements to the protonmore » beam and, hence considerably improve economic characteristics of the electronuclear reactor.« less

HEAT TRANSFER AND TRITIUM PRODUCING SYSTEM

DOEpatents

Johnson, E.F.

1962-06-01

This invention related to a circulating lithium-containing blanket system in a neution source hav'ing a magnetic field associated therewith. The blanket serves simultaneously and efficiently as a heat transfer mediunm and as a source of tritium. The blanket is composed of a lithium-6-enriched fused salt selected from the group consisting of lithium nitrite, lithium nitrate, a mixture of said salts, a mixture of each of said salts with lithium oxide, and a mixture of said salts with each other and with lithium oxide. The moderator, which is contained within the blanket in a separate conduit, can be water. A stellarator is one of the neutron sources which can be used in this invention. (AEC)

Accelerator-Driven Subcritical System for Disposing of the U.S. Spent Nuclear Fuel Inventory

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

Gohar, Yousry; Cao, Yan; Kraus, Adam R.

The current United States inventory of the spent nuclear fuel (SNF) is ~80,000 metric tons of heavy metal (MTHM), including ~131 tons of minor actinides (MAs) and ~669 tons of plutonium. This study describes a conceptual design of an accelerator-driven subcritical (ADS) system for disposing of this SNF inventory by utilizing the 131 tons of MAs inventory and a fraction of the plutonium inventory for energy production, and transmuting some long-lived fission products. An ADS system with a homogeneous subcritical fission blanket was first examined. A spallation neutron source is used to drive the blanket and it is produced frommore » the interaction of a 1-GeV proton beam with a lead-bismuth eutectic (LBE) target. The blanket has a liquid mobile fuel using LBE as the fuel carrier. The fuel materials are dissolved, mixed, or suspended in the liquid fuel carrier. Monte Carlo analyses were performed to determine the overall parameters of the concept. Steady-state Monte Carlo simulations were performed for three similar fission blankets. Except for, the loaded amount of actinide materials in the LBE is either 5, 7, or 10% of the total volume of the blanket, respectively. The neutron multiplication factors of the three blankets are ~0.98 and the initial MAs blanket inventories are ~10 tons. In addition, Monte Carlo burnup simulations using the MCB5 code were performed to analyze the performance of the three conceptual ADS systems. During operation, fresh fuel was fed into the fission blanket to adjust its reactivity and to control the system power. The burnup analysis shows that the three ADS concepts consume about 1.2 tons of actinides per full power year and produce 3 GW thermal power, with a proton beam power of 25 MW. For the blankets with 5, 7, or 10% actinide fuel particles loaded in the LBE, assuming that the ADS systems can be operated for 35 full-power years, the total MA materials consumed in the three ADS systems are about 30.6, 35.3, and 37.2 tons, respectively. Thus, the corresponding numbers of ADS systems to utilize the 131 tons of MA materials of the SNF inventory are 4.3, 3.7, or 3.5, respectively. ADS concepts with tube bundles inserted in the fission blanket were analyzed to overcome the disadvantages of the homogeneous blanket concept. The liquid lead is used as the target material, the mobile fuel carrier, and the primary coolant to avoid the polonium production from bismuth. Reactor physics and thermal-hydraulic analyses were coupled to determine the parameters of the heterogeneous fission blanket. The engineering requirements for a satisfactory operation performance of the HT-9 ferritic steel structure material have been realized. Two heterogeneous concepts of the subcritical fission blanket with the liquid lead mobile fuel inside or outside the tube bundles were considered. The heterogeneous configuration with the mobile fuel inside the tubes showed better performance than the configuration with mobile fuel outside the bundle tubes. The Monte Carlo burnup codes, MCB5 and SERPENT were both used to simulate the fuel burnup in the ADS concepts with the mobile fuels inside the tubes. The burnup analyses were carried out for 35 full power years. The results show that 5 ADS systems can dispose of the total United States inventory of the spent nuclear fuel.« less

Effects of the LDEF environment on the Ag/FEP thermal blankets

NASA Technical Reports Server (NTRS)

Levadou, Francois; Pippin, H. Gary

1992-01-01

This presentation was made by Francois Levadou at the NASA Langley Research Center LDEF materials workshop, November 19-22, 1991. It represents the results to date on the examination of silvered teflon thermal blankets primarily from the Ultra-heavy Cosmic Ray Experiment and also from the blanket from the Park Seed Company experiment. ESA/ESTEC and Boeing conducted a number of independent measurements on the blankets and in particular on the exposed fluorinated ethylene-propylene (FEP) layer of the blankets. Mass loss, thickness, and thickness profile measurements have been used by ESA, Boeing, and NASA LeRC to determine recession and average erosion yield under atomic oxygen exposure. Tensile strength and percent elongation to failure data, surface characterization by ESCA, and SEM images are presented. The Jet Propulsion Laboratory analysis of vacuum radiation effects is also presented. The results obtained by the laboratories mentioned and additional results from the Aerospace Corporation on samples provided by Boeing are quite similar and give confidence in the validity of the data.

Aerogel Blanket Insulation Materials for Cryogenic Applications

NASA Technical Reports Server (NTRS)

Coffman, B. E.; Fesmire, J. E.; White, S.; Gould, G.; Augustynowicz, S.

2009-01-01

Aerogel blanket materials for use in thermal insulation systems are now commercially available and implemented by industry. Prototype aerogel blanket materials were presented at the Cryogenic Engineering Conference in 1997 and by 2004 had progressed to full commercial production by Aspen Aerogels. Today, this new technology material is providing superior energy efficiencies and enabling new design approaches for more cost effective cryogenic systems. Aerogel processing technology and methods are continuing to improve, offering a tailor-able array of product formulations for many different thermal and environmental requirements. Many different varieties and combinations of aerogel blankets have been characterized using insulation test cryostats at the Cryogenics Test Laboratory of NASA Kennedy Space Center. Detailed thermal conductivity data for a select group of materials are presented for engineering use. Heat transfer evaluations for the entire vacuum pressure range, including ambient conditions, are given. Examples of current cryogenic applications of aerogel blanket insulation are also given. KEYWORDS: Cryogenic tanks, thermal insulation, composite materials, aerogel, thermal conductivity, liquid nitrogen boil-off

An electrically conductive thermal control surface for spacecraft encountering Low-Earth Orbit (LEO) atomic oxygen indium tin oxide-coated thermal blankets

NASA Technical Reports Server (NTRS)

Bauer, J. L.

1987-01-01

An organic black thermal blanket material was coated with indium tin oxide (ITO) to prevent blanket degradation in the low Earth orbit (LEO) atomic oxygen environment. The blankets were designed for the Galileo spacecraft. Galileo was initially intended for space shuttle launch and would, therefore, have been exposed to atomic oxygen in LEO for between 10 and 25 hours. Two processes for depositing ITO are described. Thermooptical, electrical, and chemical properties of the ITO film are presented as a function of the deposition process. Results of exposure of the ITO film to atomic oxygen (from a shuttle flight) and radiation exposure (simulated Jovian environment) are also presented. It is shown that the ITO-protected thermal blankets would resist the anticipated LEO oxygen and Jovian radiation yet provide adequate thermooptical and electrical resistance. Reference is made to the ESA Ulysses spacecraft, which also used ITO protection on thermal control surfaces.

Evaluations of Silica Aerogel-Based Flexible Blanket as Passive Thermal Control Element for Spacecraft Applications

NASA Astrophysics Data System (ADS)

Hasan, Mohammed Adnan; Rashmi, S.; Esther, A. Carmel Mary; Bhavanisankar, Prudhivi Yashwantkumar; Sherikar, Baburao N.; Sridhara, N.; Dey, Arjun

2018-03-01

The feasibility of utilizing commercially available silica aerogel-based flexible composite blankets as passive thermal control element in applications such as extraterrestrial environments is investigated. Differential scanning calorimetry showed that aerogel blanket was thermally stable over - 150 to 126 °C. The outgassing behavior, e.g., total mass loss, collected volatile condensable materials, water vapor regained and recovered mass loss, was within acceptable range recommended for the space applications. ASTM tension and tear tests confirmed the material's mechanical integrity. The thermo-optical properties remained nearly unaltered in simulated space environmental tests such as relative humidity, thermal cycling and thermo-vacuum tests and confirmed the space worthiness of the aerogel. Aluminized Kapton stitched or anchored to the blanket could be used to control the optical transparency of the aerogel. These outcomes highlight the potential of commercial aerogel composite blankets as passive thermal control element in spacecraft. Structural and chemical characterization of the material was also done using scanning electron microscopy, Fourier transform infrared spectroscopy and x-ray photoelectron spectroscopy.

Acoustic contributions of a sound absorbing blanket placed in a double panel structure: absorption versus transmission.

PubMed

Doutres, Olivier; Atalla, Noureddine

2010-08-01

The objective of this paper is to propose a simple tool to estimate the absorption vs. transmission loss contributions of a multilayered blanket unbounded in a double panel structure and thus guide its optimization. The normal incidence airborne sound transmission loss of the double panel structure, without structure-borne connections, is written in terms of three main contributions; (i) sound transmission loss of the panels, (ii) sound transmission loss of the blanket and (iii) sound absorption due to multiple reflections inside the cavity. The method is applied to four different blankets frequently used in automotive and aeronautic applications: a non-symmetric multilayer made of a screen in sandwich between two porous layers and three symmetric porous layers having different pore geometries. It is shown that the absorption behavior of the blanket controls the acoustic behavior of the treatment at low and medium frequencies and its transmission loss at high frequencies. Acoustic treatment having poor sound absorption behavior can affect the performance of the double panel structure.

Myelogenous leukemia and electric blanket use.

PubMed

Preston-Martin, S; Peters, J M; Yu, M C; Garabrant, D H; Bowman, J D

1988-01-01

In a case-control study of adult acute and chronic myelogenous leukemia in Los Angeles County, we tested the hypothesis that excess exposure to electromagnetic fields from electric blankets was associated with risk of leukemia. We did this by studying 116 cases of acute myelogenous leukemia (AML) and 108 cases of chronic myelogenous leukemia (CML) along with matched neighborhood controls. The cases and controls were queried as to electric blanket use and the risks computed. For AML the risk was 0.9 (95% CI 0.5-1.6) and for CML the risk was 0.8 (95% CI 0.4-1.6). Cases did not differ from controls by duration of use, year of first regular use, year since last use, or socioeconomic status. Our best estimates of exposure indicate that electric blanket use increases overall exposure to electric fields by less than 50% and magnetic fields by less than 100%. We conclude that there is no major leukemogenic risk associated with electric blanket use in Los Angeles County.

Lightweight Thermal Insulation for a Liquid-Oxygen Tank

NASA Technical Reports Server (NTRS)

Willen, G. Scott; Lock, Jennifer; Nieczkoski, Steve

2005-01-01

A proposed lightweight, reusable thermal-insulation blanket has been designed for application to a tank containing liquid oxygen, in place of a non-reusable spray-on insulating foam. The blanket would be of the multilayer-insulation (MLI) type and equipped with a pressure-regulated nitrogen purge system. The blanket would contain 16 layers in two 8-layer sub-blankets. Double-aluminized polyimide 0.3 mil (.0.008 mm) thick was selected as a reflective shield material because of its compatibility with oxygen and its ability to withstand ionizing radiation and high temperature. The inner and outer sub-blanket layers, 1 mil (approximately equals 0.025 mm) and 3 mils (approximately equals 0.076 mm) thick, respectively, would be made of the double-aluminized polyimide reinforced with aramid. The inner and outer layers would provide structural support for the more fragile layers between them and would bear the insulation-to-tank attachment loads. The layers would be spaced apart by lightweight, low-thermal-conductance netting made from polyethylene terephthalate.

Strategic Sourcing and Spend Analysis: A Case Study of the Naval Postgraduate School

DTIC Science & Technology

2014-12-01

ABBREVIATIONS ADP Administrative Processing Data AFIT Air Force Institute of Technology AT&L Acquisition, Technology, and Logistics BPA Blanket...in awarding 74 blanket purchase agreements ( BPAs ) with various discounts less than the Federal Supply Schedule (FSS) pricing. While the cost savings...the NPS contracting office can tailor specific contract vehicles, whether blanket purchase agreements ( BPAs ) 43 or IDIQs, to suit the needs of the

32 CFR Appendix C to Part 806b - DoD ‘Blanket Routine Uses’

Code of Federal Regulations, 2013 CFR

2013-07-01

... 32 National Defense 6 2013-07-01 2013-07-01 false DoD âBlanket Routine Usesâ C Appendix C to Part... PRIVACY ACT PROGRAM Pt. 806b, App. C Appendix C to Part 806b—DoD ‘Blanket Routine Uses’ Certain DoD... the issuance of a license, grant, or other benefit. c. Disclosure of Requested Information Routine Use...

32 CFR Appendix C to Part 806b - DoD ‘Blanket Routine Uses’

Code of Federal Regulations, 2011 CFR

2011-07-01

... 32 National Defense 6 2011-07-01 2011-07-01 false DoD âBlanket Routine Usesâ C Appendix C to Part... PRIVACY ACT PROGRAM Pt. 806b, App. C Appendix C to Part 806b—DoD ‘Blanket Routine Uses’ Certain DoD... the issuance of a license, grant, or other benefit. c. Disclosure of Requested Information Routine Use...

Influence of nuclear data uncertainties on thorium fusion-fission hybrid blanket nucleonic performance

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

Cheng, E.T.; Mathews, D.R.

1979-09-01

The fusion-fission hybrid blanket proposed for the Tandem Mirror Hybrid Reactor employs thorium metal as the fertile material. Based on the ENDF/B-IV nuclear data, the /sup 233/U and tritium production rate and blanket energy multiplication averaged over the blanket lifetime of about 9 MW-yr/m/sup 2/ are 0.76 and 1.12 per D-T neutron and 4.8, respectively. At the time of the blanket discharge, the /sup 233/U enrichment in the thorium metal is about 3%. The thorium cross sections given by the ENDF/B-IV and V were reviewed, and the important partial cross sections such as (n,2n), (n,3n), and (n,..gamma..) were found tomore » be known to +-10 to 20% in the respective energy range of interest. A sensitivity study showed that the /sup 233/U and tritium production rate and blanket energy multiplication are relatively sensitive to the thorium capture and fission cross section uncertainties. In order to predict the above parameters within +-1%, the Th(n,..gamma..) and Th(n,..nu..f) cross sections must be measured within about +-2% in the energy range 3 to 3000 keV and 13.5 to 15 MeV, respectively.« less

MHD work related to a self-cooled Pb-17Li blanket with poloidal-radial-toroidal ducts

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

Reimann, J.; Barleon, L.; Buehler, L.

1994-12-31

For self cooled liquid metal blankets MHD pressure drop and velocity distributions are considered as critical issues. This paper summarizes MHD work performed for a DEMO-relevant Pb-17Li blanket which uses essential characteristics of a previous ANL design: The coolant flows downwards in the rear poloidal ducts, turns by 180{degrees} at the blanket bottom and is distributed from the ascending poloidal ducts into short radial channels which feed the toroidal First Wall coolant ducts (aligned with the main magnetic field direction). The flow through the subsequent radial channels is collected again in poloidal channels and the coolant leaves the blanket segmentmore » at the top. The blanket design is based on the use of flow channel inserts (FCIs) (which means electrically thin conducting walls for MHD) for all ducts except for the toroidal FW coolant channels. MHD related issues were defined and estimations of corresponding pressure drops were performed. Previous experimental work included a proof of principle of FCIs and a detailed experiment with a single {open_quotes}poloidal{sm_bullet}toroidal{sm_bullet}poloidal{close_quotes} duct (cooperation with ANL). In parallel, a numerical code based on the Core Flow Approximation (CFA) was developed to predict pressure drop and velocity distributions for arbitrary single duct geometries.« less

Assessing Ink Transfer Performance of Gravure-Offset Fine-Line Circuitry Printing

NASA Astrophysics Data System (ADS)

Cheng, Hsien-Chie; Chen, You-Wei; Chen, Wen-Hwa; Lu, Su-Tsai; Lin, Shih-Ming

2018-03-01

In this study, the printing mechanism and performance of gravure-offset fine-line circuitry printing technology are investigated in terms of key printing parameters through experimental and theoretical analyses. First, the contact angles of the ink deposited on different substrates, blankets, and gravure metal plates are experimentally determined; moreover, their temperature and solvent content dependences are analyzed. Next, the ink solvent absorption and evaporation behaviors of the blankets at different temperatures, times, and numbers of printing repetitions are characterized by conducting experiments. In addition, while printing repeatedly, the surface characteristics of the blankets, such as the contact angle, vary with the amount of absorbed ink solvent, further affecting the ink transfer performance (ratio) and printing quality. Accordingly, the surface effect of the blanket due to ink solvent absorption on the ink contact angle is analyzed. Furthermore, the amount of ink transferred from the gravure plate to the blanket in the "off process" and from the blanket to the substrate in the "set process" is evaluated by conducting a simplified plate-to-plate experiment. The influences of loading rate (printing velocity), temperature, and solvent content on the ink transfer performance are addressed. Finally, the ink transfer mechanism is theoretically analyzed for different solvent contents using Surface Evolver. The calculation results are compared with those of the experiment.

KSC-08pd2288

NASA Image and Video Library

2008-08-05

CAPE CANAVERAL, Fla. – The Multi-Use Lightweight Equipment (MULE) carrier arrives at NASA's Kennedy Space Center for the fifth and final shuttle servicing mission to NASA's Hubble Space Telescope, STS-125. The MULE carrier will join the Flight Support System, the Super Lightweight Interchangeable Carrier and the Orbital Replacement Unit Carrier in the Payload Hazardous Servicing Facility where the Hubble payload is being prepared for launch. The Relative Navigation Sensors and the New Outer Blanket Layers will be on the MULE. The payload is scheduled to go to Launch Pad 39A in mid-September to be installed into Atlantis' payload bay. Atlantis is targeted to launch Oct. 8 at 1:34 a.m. EDT. .Photo credit: NASA/Amanda Diller

KSC-04PD-0428

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. At the Astrotech Space Operations processing facilities near KSC, workers begin moving NASAs MESSENGER spacecraft into the building MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging is being taken into a high bay clean room where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-04PD-0430

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers get ready to remove the protective cover from NASAs MESSENGER spacecraft. Employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-04PD-0427

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. At the Astrotech Space Operations processing facilities near KSC, workers check the moveable pallet holding NASAs MESSENGER spacecraft. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be taken into a high bay clean room and employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-04PD-0436

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers prepare NASAs MESSENGER spacecraft for transfer to a work stand. There employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-2012-3436

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, a technician installs protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-2012-3437

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, a technician installs protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-2012-3430

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, technicians prepare to install protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-2012-3439

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, a technician installs protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-2012-3435

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, a technician installs protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-2012-3433

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, a technician installs protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-2012-3432

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, a technician installs protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-2012-3434

NASA Image and Video Library

2012-06-21

CAPE CANAVERAL, Fla. – Inside the Astrotech payload processing facility near NASA’s Kennedy Space Center in Florida, a technician installs protective thermal blankets around the Radiation Belt Storm Probes, or RBSP, spacecraft A. NASA’s RBSP mission will help us understand the sun’s influence on Earth and near-Earth space by studying the Earth’s radiation belts on various scales of space and time. RBSP will begin its mission of exploration of Earth’s Van Allen radiation belts and the extremes of space weather after its launch aboard a United Launch Alliance Atlas V rocket. Launch is targeted for Aug. 23. For more information, visit http://www.nasa.gov/rbsp. Photo credit: NASA/Kim Shiflett

KSC-08pd1032

NASA Image and Video Library

2008-04-25

CAPE CANAVERAL, Fla. – At the Astrotech payload processing facility, technicians install insulation blankets around the star tracker sunshades on NASA's Gamma-ray Large Area Space Telescope, or GLAST, spacecraft. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date is still to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1031

NASA Image and Video Library

2008-04-25

CAPE CANAVERAL, Fla. – At the Astrotech payload processing facility, technicians install insulation blankets around the star tracker sunshades on NASA's Gamma-ray Large Area Space Telescope, or GLAST, spacecraft. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date is still to be determined. Photo credit: NASA/Jim Grossmann

KSC-08pd1033

NASA Image and Video Library

2008-04-25

CAPE CANAVERAL, Fla. – At the Astrotech payload processing facility, technicians install insulation blankets around the star tracker sunshades on NASA's Gamma-ray Large Area Space Telescope, or GLAST, spacecraft. The GLAST is a powerful space observatory that will explore the Universe's ultimate frontier, where nature harnesses forces and energies far beyond anything possible on Earth; probe some of science's deepest questions, such as what our Universe is made of, and search for new laws of physics; explain how black holes accelerate jets of material to nearly light speed; and help crack the mystery of stupendously powerful explosions known as gamma-ray bursts. A launch date is still to be determined. Photo credit: NASA/Jim Grossmann

Assembly, Integration, and Test Methods for Operationally Responsive Space Satellites

DTIC Science & Technology

2010-03-01

like assembly and vibration tests, to ensure there have been no failures induced by the activities. External thermal control blankets and radiator...configuration of the satellite post- vibration test and adds time to the process. • Thermal blanketing is not realistic with current technology or...patterns for thermal blankets and radiator tape. The computer aided drawing (CAD) solid model was used to generate patterns that were cut and applied real

LIFE Materials: Thermomechanical Effects Volume 5 - Part I

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

Caro, M; DeMange, P; Marian, J

2009-05-07

Improved fuel performance is a key issue in the current Laser Inertial-Confinement Fusion-Fission Energy (LIFE) engine design. LIFE is a fusion-fission engine composed of a {approx}40-tons fuel blanket surrounding a pulsed fusion neutron source. Fusion neutrons get multiplied and moderated in a Beryllium blanket before penetrating the subcritical fission blanket. The fuel in the blanket is composed of millions of fuel pebbles, and can in principle be burned to over 99% FIMA without refueling or reprocessing. This report contains the following chapters: Chapter A: LIFE Requirements for Materials -- LIFE Fuel; Chapter B: Summary of Existing Knowledge; Chapter C: Identificationmore » of Gaps in Knowledge & Vulnerabilities; and Chapter D: Strategy and Future Work.« less

Design of an arc-free thermal blanket

NASA Technical Reports Server (NTRS)

Fellas, C. N.

1981-01-01

The success of a multilayer thermal blanket in eliminating arcing is discussed. Arcing is eliminated by limiting the surface potential to well below the threshold level for discharge. This is achieved by enhancing the leakage current which results in conduction of the excess charge to the spacecraft structure. The thermal blanket consists of several layers of thermal control (space approved) materials, bonded together, with Kapton on the outside, arranged in such a way that when the outer surface is charged by electron irradiation, a strong electric field is set up on the Kapton layer resulting in a greatly improved conductivity. The basic properties of matter utilized in designing this blanket method of charge removal, and optimum thermo-optical properties are summarized.

Key achievements in elementary R&D on water-cooled solid breeder blanket for ITER test blanket module in JAERI

NASA Astrophysics Data System (ADS)

Suzuki, S.; Enoeda, M.; Hatano, T.; Hirose, T.; Hayashi, K.; Tanigawa, H.; Ochiai, K.; Nishitani, T.; Tobita, K.; Akiba, M.

2006-02-01

This paper presents the significant progress made in the research and development (R&D) of key technologies on the water-cooled solid breeder blanket for the ITER test blanket modules in JAERI. Development of module fabrication technology, bonding technology of armours, measurement of thermo-mechanical properties of pebble beds, neutronics studies on a blanket module mockup and tritium release behaviour from a Li2TiO3 pebble bed under neutron-pulsed operation conditions are summarized. With the improvement of the heat treatment process for blanket module fabrication, a fine-grained microstructure of F82H can be obtained by homogenizing it at 1150 °C followed by normalizing it at 930 °C after the hot isostatic pressing process. Moreover, a promising bonding process for a tungsten armour and an F82H structural material was developed using a solid-state bonding method based on uniaxial hot compression without any artificial compliant layer. As a result of high heat flux tests of F82H first wall mockups, it has been confirmed that a fatigue lifetime correlation, which was developed for the ITER divertor, can be made applicable for the F82H first wall mockup. As for R&D on the breeder material, Li2TiO3, the effect of compression loads on effective thermal conductivity of pebble beds has been clarified for the Li2TiO3 pebble bed. The tritium breeding ratio of a simulated multi-layer blanket structure has successfully been measured using 14 MeV neutrons with an accuracy of 10%. The tritium release rate from the Li2TiO3 pebble has also been successfully measured with pulsed neutron irradiation, which simulates ITER operation.

Analyses of Hubble Space Telescope Aluminized-Teflon Multilayer Insulation Blankets Retrieved After 19 Years of Space Exposure

NASA Technical Reports Server (NTRS)

de Groh, Kim K.; Perry, Bruce A.; Mohammed, Jelila S.; Banks, Bruce

2015-01-01

Since its launch in April 1990, the Hubble Space Telescope (HST) has made many important observations from its vantage point in low Earth orbit (LEO). However, as seen during five servicing missions, the outer layer of multilayer insulation (MLI) has become increasingly embrittled and has cracked in many areas. In May 2009, during the 5th servicing mission (called SM4), two MLI blankets were replaced with new insulation and the space-exposed MLI blankets were retrieved for degradation analyses by teams at NASA Glenn Research Center (GRC) and NASA Goddard Space Flight Center (GSFC). The retrieved MLI blankets were from Equipment Bay 8, which received direct sunlight, and Equipment Bay 5, which received grazing sunlight. Each blanket was divided into several regions based on environmental exposure and/or physical appearance. The aluminized-Teflon (DuPont, Wilmington, DE) fluorinated ethylene propylene (Al-FEP) outer layers of the retrieved MLI blankets have been analyzed for changes in optical, physical, and mechanical properties, along with chemical and morphological changes. Pristine and as-retrieved samples (materials) were heat treated to help understand degradation mechanisms. When compared to pristine material, the analyses have shown how the Al-FEP was severely affected by the space environment. Most notably, the Al-FEP was highly embrittled, fracturing like glass at strains of 1 to 8 percent. Across all measured properties, more significant degradation was observed for Bay 8 material as compared to Bay 5 material. This paper reviews the tensile and bend-test properties, density, thickness, solar absorptance, thermal emittance, x-ray photoelectron spectroscopy (XPS) and energy dispersive spectroscopy (EDS) elemental composition measurements, surface and crack morphologies, and atomic oxygen erosion yields of the Al-FEP outer layer of the retrieved HST blankets after 19 years of space exposure.

A computational investigation of the interstitial flow induced by a variably thick blanket of very fine sand covering a coarse sand bed

NASA Astrophysics Data System (ADS)

Bartzke, Gerhard; Huhn, Katrin; Bryan, Karin R.

2017-10-01

Blanketed sediment beds can have different bed mobility characteristics relative to those of beds composed of uniform grain-size distribution. Most of the processes that affect bed mobility act in the direct vicinity of the bed or even within the bed itself. To simulate the general conditions of analogue experiments, a high-resolution three-dimensional numerical `flume tank' model was developed using a coupled finite difference method flow model and a discrete element method particle model. The method was applied to investigate the physical processes within blanketed sediment beds under the influence of varying flow velocities. Four suites of simulations, in which a matrix of uniform large grains (600 μm) was blanketed by variably thick layers of small particles (80 μm; blanket layer thickness approx. 80, 350, 500 and 700 μm), were carried out. All beds were subjected to five predefined flow velocities ( U 1-5=10-30 cm/s). The fluid profiles, relative particle distances and porosity changes within the bed were determined for each configuration. The data show that, as the thickness of the blanket layer increases, increasingly more small particles accumulate in the indentations between the larger particles closest to the surface. This results in decreased porosity and reduced flow into the bed. In addition, with increasing blanket layer thickness, an increasingly larger number of smaller particles are forced into the pore spaces between the larger particles, causing further reduction in porosity. This ultimately causes the interstitial flow, which would normally allow entrainment of particles in the deeper parts of the bed, to decrease to such an extent that the bed is stabilized.

Annular seed-blanket thorium fuel core concepts for heavy water moderated reactors

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

Bromley, B.P.; Hyland, B.

2013-07-01

New reactor concepts to implement thorium-based fuel cycles have been explored to achieve maximum resource utilization. Pressure tube heavy water reactors (PT-HWR) are highly advantageous for implementing the use of thorium-based fuels because of their high neutron economy and on-line re-fuelling capability. The use of heterogeneous seed-blanket core concepts in a PT-HWR where higher-fissile-content seed fuel bundles are physically separate from lower-fissile-content blanket bundles allows more flexibility and control in fuel management to maximize the fissile utilization and conversion of fertile fuel. The lattice concept chosen is a 35-element bundle made with a homogeneous mixture of reactor grade Pu andmore » Th, and with a central zirconia rod to help reduce coolant void reactivity. Several annular heterogeneous seed-blanket core concepts with plutonium-thorium-based fuels in a 700-MWe-class PT-HWR were analyzed, using a once-through thorium (OTT) cycle. Different combinations of seed and blanket fuel were tested to determine the impact on core-average burnup, fissile utilization, power distributions, and other performance parameters. It was found that the various core concepts can achieve a fissile utilization that is up to 30% higher than is currently achieved in a PT-HWR using conventional natural uranium fuel bundles. Up to 67% of the Pu is consumed; up to 43% of the energy is produced from thorium, and up to 363 kg/year of U-233 is produced. Seed-blanket cores with ∼50% content of low-power blanket bundles may require power de-rating (∼58% to 65%) to avoid exceeding maximum limits for peak channel power, bundle power and linear element ratings. (authors)« less

Improved structure and long-life blanket concepts for heliotron reactors

NASA Astrophysics Data System (ADS)

Sagara, A.; Imagawa, S.; Mitarai, O.; Dolan, T.; Tanaka, T.; Kubota, Y.; Yamazaki, K.; Watanabe, K. Y.; Mizuguchi, N.; Muroga, T.; Noda, N.; Kaneko, O.; Yamada, H.; Ohyabu, N.; Uda, T.; Komori, A.; Sudo, S.; Motojima, O.

2005-04-01

New design approaches are proposed for the LHD-type heliotron D-T demo-reactor FFHR2 to solve the key engineering issues of blanket space limitation and replacement difficulty. A major radius of over 14 m is selected to permit a blanket-shield thickness of about 1 m and to reduce the neutron wall loading and toroidal field, while achieving an acceptable cost of electricity. Two sets of optimization are successfully carried out. One is to reduce the magnetic hoop force on the helical coil support structures by adjustment of the helical winding coil pitch parameter and the poloidal coils design, which facilitates expansion of the maintenance ports. The other is a long-life blanket concept using carbon armour tiles that soften the neutron energy spectrum incident on the self-cooled flibe-reduced activation ferritic steel blanket. In this adaptation of the spectral-shifter and tritium breeder blanket (STB) concept a local tritium breeding ratio over 1.2 is feasible by optimized arrangement of the neutron multiplier Be in the carbon tiles, and the radiation shielding of the superconducting magnet coils is also significantly improved. Using constant cross sections of a helically winding shape, the 'screw coaster' concept is proposed to replace in-vessel components such as the STB armour tiles. The key R&D issues for developing the STB concept, such as radiation effects on carbon and enhanced heat transfer of Flibe, are elucidated.

Modeling and Simulation of the ITER First Wall/Blanket Primary Heat Transfer System

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

Ying, Alice; Popov, Emilian L

2011-01-01

ITER inductive power operation is modeled and simulated using a thermal-hydraulics system code (RELAP5) integrated with a 3-D CFD (SC-Tetra) code. The Primary Heat Transfer System (PHTS) functions are predicted together with the main parameters operational ranges. The control algorithm strategy and derivation are summarized as well. The First Wall and Blanket modules are the primary components of PHTS, used to remove the major part of the thermal heat from the plasma. The modules represent a set of flow channels in solid metal structure that serve to absorb the radiation heat and nuclear heating from the fusion reactions and tomore » provide shield for the vacuum vessel. The blanket modules are water cooled. The cooling is forced convective with constant blanket inlet temperature and mass flow rate. Three independent water loops supply coolant to the three blanket sectors. The main equipment of each loop consists of a pump, a steam pressurizer and a heat exchanger. A major feature of ITER is the pulsed operation. The plasma does not burn continuously, but on intervals with large periods of no power between them. This specific feature causes design challenges to accommodate the thermal expansion of the coolant during the pulse period and requires active temperature control to maintain a constant blanket inlet temperature.« less

Analyses of Hubble Space Telescope Aluminized-Teflon Insulation Retrieved After 19 Years of Space Exposure

NASA Technical Reports Server (NTRS)

deGroh, Kim K.; Waters, Deborah L.; Mohammed, Jelila S.; Perry, Bruce A.; Banks, Bruce A.

2012-01-01

Since its launch in April 1990, the Hubble Space Telescope (HST) has made many important observations from its vantage point in low Earth orbit (LEO). However, as seen during five servicing missions, the outer layer of multilayer insulation (MLI) has become successively more embrittled and has cracked in many areas. In May 2009, during the 5th servicing mission (called SM4), two MLI blankets were replaced with new insulation pieces and the space-exposed MLI blankets were retrieved for degradation analyses by teams at NASA Glenn Research Center (GRC) and NASA Goddard Space Flight Center (GSFC). The MLI blankets were from Equipment Bay 8, which received direct sunlight, and Equipment Bay 5, which received grazing sunlight. Each blanket contained a range of unique regions based on environmental exposure and/or physical appearance. The retrieved MLI blanket s aluminized-Teflon (DuPont) fluorinated ethylene propylene (Al-FEP) outer layers have been analyzed for changes in optical, physical, and mechanical properties, along with space induced chemical and morphological changes. When compared to pristine material, the analyses have shown how the Al-FEP was severely affected by the space environment. This paper reviews tensile properties, solar absorptance, thermal emittance, x-ray photoelectron spectroscopy (XPS) data and atomic oxygen erosion values of the retrieved HST blankets after 19 years of space exposure.

A Proposed Methodology to Control Body Temperature in Patients at Risk of Hypothermia by means of Active Rewarming Systems

PubMed Central

Costanzo, Silvia; Cusumano, Alessia; Giaconia, Carlo; Mazzacane, Sante

2014-01-01

Hypothermia is a common complication in patients undergoing surgery under general anesthesia. It has been noted that, during the first hour of surgery, the patient's internal temperature (T core) decreases by 0.5–1.5°C due to the vasodilatory effect of anesthetic gases, which affect the body's thermoregulatory system by inhibiting vasoconstriction. Thus a continuous check on patient temperature must be carried out. The currently most used methods to avoid hypothermia are based on passive systems (such as blankets reducing body heat loss) and on active ones (thermal blankets, electric or hot-water mattresses, forced hot air, warming lamps, etc.). Within a broader research upon the environmental conditions, pollution, heat stress, and hypothermia risk in operating theatres, the authors set up an experimental investigation by using a warming blanket chosen from several types on sale. Their aim was to identify times and ways the human body reacts to the heat flowing from the blanket and the blanket's effect on the average temperature T skin and, as a consequence, on T core temperature of the patient. The here proposed methodology could allow surgeons to fix in advance the thermal power to supply through a warming blanket for reaching, in a prescribed time, the desired body temperature starting from a given state of hypothermia. PMID:25485278

Economics of movable interior blankets for greenhouses

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

White, G.B.; Fohner, G.R.; Albright, L.D.

1981-01-01

A model for evaluating the economic impact of investment in a movable interior blanket was formulated. The method of analysis was net present value (NPV), in which the discounted, after-tax cash flow of costs and benefits was computed for the useful life of the system. An added feature was a random number component which permitted any or all of the input parameters to be varied within a specified range. Results from 100 computer runs indicated that all of the NPV estimates generated were positive, showing that the investment was profitable. However, there was a wide range of NPV estimates, frommore » $16.00/m/sup 2/ to $86.40/m/sup 2/, with a median value of $49.34/m/sup 2/. Key variables allowed to range in the analysis were: (1) the cost of fuel before the blanket is installed; (2) the percent fuel savings resulting from use of the blanket; (3) the annual real increase in the cost of fuel; and (4) the change in the annual value of the crop. The wide range in NPV estimates indicates the difficulty in making general recommendations regarding the economic feasibility of the investment when uncertainty exists as to the correct values for key variables in commercial settings. The results also point out needed research into the effect of the blanket on the crop, and on performance characteristics of the blanket.« less

Advanced Multifunctional MMOD Shield: Radiation Shielding Assessment

NASA Technical Reports Server (NTRS)

Rojdev, Kristina; Christiansen, Eric

2013-01-01

As NASA is looking to explore further into deep space, multifunctional materials are a necessity for decreasing complexity and mass. One area where multifunctional materials could be extremely beneficial is in the micrometeoroid orbital debris (MMOD) shield. A typical MMOD shield on the International Space Station (ISS) is a stuffed whipple shield consisting of multiple layers. One of those layers is the thermal blanket, or multi-layer insulation (MLI). Increasing the MMOD effectiveness of MLI blankets, while still preserving their thermal capabilities, could allow for a less massive MMOD shield. Thus, a study was conducted to evaluate a concept MLI blanket for an MMOD shield. In conjunction, this MLI blanket and the subsequent MMOD shield was also evaluated for its radiation shielding effectiveness towards protecting crew. The overall MMOD shielding system using the concept MLI blanket proved to only have a marginal increase in the radiation mitigating properties. Therefore, subsequent analysis was performed on various conceptual MMOD shields to determine the combination of materials that may prove superior for radiation mitigating purposes. The following paper outlines the evaluations performed and discusses the results and conclusions of this evaluation for radiation shielding effectiveness.

Fusion neutron source blanket: requirements for calculation accuracy and benchmark experiment precision

NASA Astrophysics Data System (ADS)

Zhirkin, A. V.; Alekseev, P. N.; Batyaev, V. F.; Gurevich, M. I.; Dudnikov, A. A.; Kuteev, B. V.; Pavlov, K. V.; Titarenko, Yu. E.; Titarenko, A. Yu.

2017-06-01

In this report the calculation accuracy requirements of the main parameters of the fusion neutron source, and the thermonuclear blankets with a DT fusion power of more than 10 MW, are formulated. To conduct the benchmark experiments the technical documentation and calculation models were developed for two blanket micro-models: the molten salt and the heavy water solid-state blankets. The calculations of the neutron spectra, and 37 dosimetric reaction rates that are widely used for the registration of thermal, resonance and threshold (0.25-13.45 MeV) neutrons, were performed for each blanket micro-model. The MCNP code and the neutron data library ENDF/B-VII were used for the calculations. All the calculations were performed for two kinds of neutron source: source I is the fusion source, source II is the source of neutrons generated by the 7Li target irradiated by protons with energy 24.6 MeV. The spectral indexes ratios were calculated to describe the spectrum variations from different neutron sources. The obtained results demonstrate the advantage of using the fusion neutron source in future experiments.

Study of the effects of corrugated wall structures due to blanket modules around ICRH antennas

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

Dumortier, Pierre; Louche, Fabrice; Messiaen, André

2014-02-12

In future fusion reactors, and in ITER, the first wall will be covered by blanket modules. These blanket modules, whose dimensions are of the order of the ICRF wavelengths, together with the clearance gaps between them will constitute a corrugated structure which will interact with the electromagnetic waves launched by ICRF antennas. The conditions in which the grooves constituted by the clearance gaps between the blanket modules can become resonant are studied. Simple analytical models and numerical simulations show that mushroom type structures (with larger gaps at the back than at the front) can bring down the resonance frequencies, whichmore » could lead to large voltages in the gaps between the blanket modules and perturb the RF properties of the antenna if they are in the ICRF operating range. The effect on the wave propagation along the wall structure, which is acting as a spatially periodic (toroidally and poloidally) corrugated structure, and hence constitutes a slow wave structure modifying the wall boundary condition, is examined.« less

First-wall structural analysis of the self-cooled water blanket concept

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

O'Brien, D.A.; Steiner, D.; Embrechts, M.J.

1986-01-01

A novel blanket concept recently proposed utilizes water with small amounts of dissolved lithium compound as both coolant and breeder. The inherent simplicity of this idea should result in an attractive breeding blanket for fusion reactors. In addition, the available base of relevant information accumulated through water-cooled fission reactor programs should greatly facilitate the R and D effort required to validate this concept. First-wall and blanket designs have been developed first for the tandem mirror reactor (TMR) due to the obvious advantages of this geometry. First-wall and blanket designs will also be developed for toroidal reactors. A simple plate designmore » with coolant tubes welded on the back (side away from plasma) was chosen as the first wall for the TMR application. Dimensions and materials were chosen to minimize temperature differences and thermal stresses. A finite element code (STRAW), originally developed for the analysis of core components subjected to high-pressure transients in the fast breeder program, was utilized to evaluate stresses in the first wall.« less

On the use of tin?lithium alloys as breeder material for blankets of fusion power plants

NASA Astrophysics Data System (ADS)

Fütterer, M. A.; Aiello, G.; Barbier, F.; Giancarli, L.; Poitevin, Y.; Sardain, P.; Szczepanski, J.; Li Puma, A.; Ruvutuso, G.; Vella, G.

2000-12-01

Tin-lithium alloys have several attractive thermo-physical properties, in particular high thermal conductivity and heat capacity, that make them potentially interesting candidates for use in liquid metal blankets. This paper presents an evaluation of the advantages and drawbacks caused by the substitution of the currently employed alloy lead-lithium (Pb-17Li) by a suitable tin-lithium alloy: (i) for the European water-cooled Pb-17Li (WCLL) blanket concept with reduced activation ferritic-martensitic steel as the structural material; (ii) for the European self-cooled TAURO blanket with SiC f/SiC as the structural material. It was found that in none of these blankets Sn-Li alloys would lead to significant advantages, in particular due to the low tritium breeding capability. Only in forced convection cooled divertors with W-alloy structure, Sn-Li alloys would be slightly more favorable. It is concluded that Sn-Li alloys are only advantageous in free surface cooled reactor internals, as this would make maximum use of the principal advantage of Sn-Li, i.e., the low vapor pressure.

Economic Analysis of Complex Nuclear Fuel Cycles with NE-COST

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

Ganda, Francesco; Dixon, Brent; Hoffman, Edward

The purpose of this work is to present a new methodology, and associated computational tools, developed within the U.S. Department of Energy (U.S. DOE) Fuel Cycle Option Campaign to quantify the economic performance of complex nuclear fuel cycles. The levelized electricity cost at the busbar is generally chosen to quantify and compare the economic performance of different baseload generating technologies, including of nuclear: it is the cost of electricity which renders the risk-adjusted discounted net present value of the investment cash flow equal to zero. The work presented here is focused on the calculation of the levelized cost of electricitymore » of fuel cycles at mass balance equilibrium, which is termed LCAE (Levelized Cost of Electricity at Equilibrium). To alleviate the computational issues associated with the calculation of the LCAE for complex fuel cycles, a novel approach has been developed, which has been called the “island approach” because of its logical structure: a generic complex fuel cycle is subdivided into subsets of fuel cycle facilities, called islands, each containing one and only one type of reactor or blanket and an arbitrary number of fuel cycle facilities. A nuclear economic software tool, NE-COST, written in the commercial programming software MATLAB®, has been developed to calculate the LCAE of complex fuel cycles with the “island” computational approach. NE-COST has also been developed with the capability to handle uncertainty: the input parameters (both unit costs and fuel cycle characteristics) can have uncertainty distributions associated with them, and the output can be computed in terms of probability density functions of the LCAE. In this paper NE-COST will be used to quantify, as examples, the economic performance of (1) current Light Water Reactors (LWR) once-through systems; (2) continuous plutonium recycling in Fast Reactors (FR) with driver and blanket; (3) Recycling of plutonium bred in FR into LWR. For each fuel cycle, the contributions to the total LCAE of the main cost components will be identified.« less

Space Station Freedom solar array panels plasma interaction test facility

NASA Technical Reports Server (NTRS)

Martin, Donald F.; Mellott, Kenneth D.

1989-01-01

The Space Station Freedom Power System will make extensive use of photovoltaic (PV) power generation. The phase 1 power system consists of two PV power modules each capable of delivering 37.5 KW of conditioned power to the user. Each PV module consists of two solar arrays. Each solar array is made up of two solar blankets. Each solar blanket contains 82 PV panels. The PV power modules provide a 160 V nominal operating voltage. Previous research has shown that there are electrical interactions between a plasma environment and a photovoltaic power source. The interactions take two forms: parasitic current loss (occurs when the currect produced by the PV panel leaves at a high potential point and travels through the plasma to a lower potential point, effectively shorting that portion of the PV panel); and arcing (occurs when the PV panel electrically discharges into the plasma). The PV solar array panel plasma interaction test was conceived to evaluate the effects of these interactions on the Space Station Freedom type PV panels as well as to conduct further research. The test article consists of two active solar array panels in series. Each panel consists of two hundred 8 cm x 8 cm silicon solar cells. The test requirements dictated specifications in the following areas: plasma environment/plasma sheath; outgassing; thermal requirements; solar simulation; and data collection requirements.

47 CFR 22.353 - Blanketing interference.

Code of Federal Regulations, 2012 CFR

2012-10-01

... Operational and Technical Requirements Technical Requirements § 22.353 Blanketing interference. Licensees of... consumer antenna systems, or the use of high gain antennas or antenna booster amplifiers by consumers. (d...

47 CFR 22.353 - Blanketing interference.

Code of Federal Regulations, 2014 CFR

2014-10-01

... Operational and Technical Requirements Technical Requirements § 22.353 Blanketing interference. Licensees of... consumer antenna systems, or the use of high gain antennas or antenna booster amplifiers by consumers. (d...

47 CFR 22.353 - Blanketing interference.

Code of Federal Regulations, 2013 CFR

2013-10-01

... Operational and Technical Requirements Technical Requirements § 22.353 Blanketing interference. Licensees of... consumer antenna systems, or the use of high gain antennas or antenna booster amplifiers by consumers. (d...

47 CFR 22.353 - Blanketing interference.

Code of Federal Regulations, 2011 CFR

2011-10-01

... Operational and Technical Requirements Technical Requirements § 22.353 Blanketing interference. Licensees of... consumer antenna systems, or the use of high gain antennas or antenna booster amplifiers by consumers. (d...

Multipurpose insulation system for a radioisotope fueled Mini-Brayton Heat Source Assembly

NASA Technical Reports Server (NTRS)

Aller, P.; Saylor, W.; Schmidt, G.; Wein, D.

1976-01-01

The Mini-Brayton Heat Source Assembly (HSA) consists of a radioisotope fueled heat source, a heat exchanger, a multifoil thermal insulation blanket, and a hermetically sealed housing. The thermal insulation blanket is a multilayer wrap of thin metal foil separated by a sparsely coated oxide. The objectives of the insulation blanket are related to the effective insulation of the HSA during operation, the transfer of the full thermal inventory to the housing when the primary coolant is not flowing, and the transfer of the full thermal inventory to the housing in the event of a flow stoppage of the primary coolant. A description is given of the approaches which have been developed to make it possible for the insulation blanket to meet these requirements.

Comfort for Sportsmen

NASA Technical Reports Server (NTRS)

1976-01-01

MPI Outdoor Safety Products developed aluminized mylar to make Echo Satellites more reflective, to insulate cryogenic fluids, and for space suit insulation. This technology has spun off to a variety of consumer products. Sportsman's blankets and jackets, ski parkas, sleeping bags, and even life-raft canopies are among them. Sportsman's blanket weighing 12 ounces can be used equally well to keep heat away or keep available heat in. Emergency rescue blanket has heat retention qualities similar to those of Sportsman's blanket. Strong enough to be used as a litter, yet folds up so small you can carry it in your shirt pocket. 10 ounce reversible jacket absorbs warmth from sun. A silver colored side next to your body retains a large portion of body heat. In warm weather you wear silver side out to reflect sun's rays.

First wall structural analysis of the aqueous self-cooled blanket concept

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

O'Brien, D.A.; Steiner, D.; Embrechts, M.J.

1986-11-01

A recently proposed blanket concept using water coolant with dissolved lithium compounds for breeding employs water cooled first walls. Water cooled first walls for blankets have also been proposed for some solid breeder blankets. Design options for water cooled first walls are examined in this paper. Four geometries and three materials are analyzed for water coolant at 300/sup 0/C and 13.8 MPa (2000 psi). Maximum neutron wall loads (with surface heat loads being 25% of neutron wall load) are determined for each geometry and material combination. Of the materials studied, only vanadium alloy is found to be capable of withstandingmore » high wall loads (>10MW/m/sup 2/ neutron and >2.5 MW/m/sup 2/ heat).« less

Vegetation cover and long-term conservation of radioactive waste packages: the case study of the CSM waste disposal facility (Manche District, France).

PubMed

Petit-Berghem, Yves; Lemperiere, Guy

2012-03-01

The CSM is the first French waste disposal facility for radioactive waste. Waste material is buried several meters deep and protected by a multi-layer cover, and equipped with a drainage system. On the surface, the plant cover is a grassland vegetation type. A scientific assessment has been carried out by the Géophen laboratory, University of Caen, in order to better characterize the plant cover (ecological groups and associated soils) and to observe its medium and long term evolution. Field assessments made on 10 plots were complemented by laboratory analyses carried out over a period of 1 year. The results indicate scenarios and alternative solutions which could arise, in order to passively ensure the long-term safety of the waste disposal system. Several proposals for a blanket solution are currently being studied and discussed, under the auspices of international research institutions in order to determine the most appropriate materials for the storage conditions. One proposal is an increased thickness of these materials associated with a geotechnical barrier since it is well adapted to the forest plants which are likely to colonize the site. The current experiments that are carried out will allow to select the best option and could provide feedback for other waste disposal facility sites already being operated in France (CSFMA waste disposal facility, Aube district) or in other countries.

KSC-04pd1852

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - Looking at damage on the second floor of the hurricane-ravaged Thermal Protection System Facility (TPSF) are (from left) Kevin Harrington, manager of Soft Goods Production, TPSF ; Martin Wilson, manager of Thermal Protection System operations for USA; Scott Kerr, KSC director of Spaceport Services; and James Kennedy, Center director. The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof during Hurricane Frances, which blew across Central Florida Sept. 4-5. Undamaged equipment was removed from the TPSF and stored in the RLV hangar. NASA Administrator Sean O’Keefe and NASA Associate Administrator of Space Operations Mission Directorate William Readdy are visiting KSC to survey the damage sustained by KSC facilities from the hurricane. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters - Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

KSC-04pd1841

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - Martin Wilson (second from right), manager of Thermal Protection System (TPS) operations for United Space Alliance (USA), briefs NASA Administrator Sean O’Keefe, KSC Director of Shuttle Processing Michael E. Wetmore and Center Director James Kennedy about the temporary tile shop set up in the RLV hangar. At far right is USA Manager of Soft Goods Production in the TPSF, Kevin Harrington. O’Keefe and NASA Associate Administrator of Space Operations Mission Directorate William Readdy are visiting KSC to survey the damage sustained by KSC facilities from Hurricane Frances. The Thermal Protection System Facility (TPSF), which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof in the storm, which blew across Central Florida Sept. 4-5. Undamaged equipment was removed from the TPSF and stored in the hangar. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters -- Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

Insulation Blankets for High-Temperature Use

NASA Technical Reports Server (NTRS)

Goldstein, H.; Leiser, D.; Sawko, P. M.; Larson, H. K.; Estrella, C.; Smith, M.; Pitoniak, F. J.

1986-01-01

Insulating blanket resists temperatures up to 1,500 degrees F (815 degrees C). Useful where high-temperature resistance, flexibility, and ease of installation are important - for example, insulation for odd-shaped furnaces and high-temperature ducts, curtains for furnace openings and fire control, and conveyor belts in hot processes. Blanket is quilted composite consisting of two face sheets: outer one of silica, inner one of silica or other glass cloth with center filling of pure silica glass felt sewn together with silica glass threads.

Preliminary Failure Modes and Effects Analysis of the US DCLL Test Blanket Module

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

Lee C. Cadwallader

2010-06-01

This report presents the results of a preliminary failure modes and effects analysis (FMEA) of a small tritium-breeding test blanket module design for the International Thermonuclear Experimental Reactor. The FMEA was quantified with “generic” component failure rate data, and the failure events are binned into postulated initiating event families and frequency categories for safety assessment. An appendix to this report contains repair time data to support an occupational radiation exposure assessment for test blanket module maintenance.

Preliminary Failure Modes and Effects Analysis of the US DCLL Test Blanket Module

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

Lee C. Cadwallader

2007-08-01

This report presents the results of a preliminary failure modes and effects analysis (FMEA) of a small tritium-breeding test blanket module design for the International Thermonuclear Experimental Reactor. The FMEA was quantified with “generic” component failure rate data, and the failure events are binned into postulated initiating event families and frequency categories for safety assessment. An appendix to this report contains repair time data to support an occupational radiation exposure assessment for test blanket module maintenance.

COUPLED FAST-THERMAL POWER BREEDER REACTOR

DOEpatents

Avery, R.

1961-07-18

A nuclear reactor having a region operating predominantly on fast neutrons and another region operating predominantly on slow neutrons is described. The fast region is a plutonium core and the slow region is a natural uranium blanket around the core. Both of these regions are free of moderator. A moderating reflector surrounds the uranium blanket. The moderating material and thickness of the reflector are selected so that fissions in the uranium blanket make a substantial contribution to the reactivity of the reactor.

Mirror plasma apparatus

DOEpatents

Moir, Ralph W.

1981-01-01

A mirror plasma apparatus which utilizes shielding by arc discharge to form a blanket plasma and lithium walls to reduce neutron damage to the wall of the apparatus. An embodiment involves a rotating liquid lithium blanket for a tandem mirror plasma apparatus wherein the first wall of the central mirror cell is made of liquid lithium which is spun with angular velocity great enough to keep the liquid lithium against the first material wall, a blanket plasma preventing the lithium vapor from contaminating the plasma.

Test Plans. Lightweight Durable TPS: Tasks 1,2,4,5, and 6

NASA Technical Reports Server (NTRS)

Greenberg, H. S.; Tu, Tina

1994-01-01

The objective of this task is to develop the fluted core flexible blankets, also referred to as the Tailorable Advanced Blanket Insulation (TABI), to a technology readiness level (TRL) of 6. This task is one of the six tasks under TA 3, Lightweight Durable TPS study, of the Single Stage to Orbit (SSTO) program. The purpose of this task is to develop a durable and low maintenance flexible TPS blanket material to be implemented on the SSTO vehicle.

FACT, Mega-ROSA, SOLAROSA

NASA Technical Reports Server (NTRS)

Spence, Brian; White, Steve; Schmid, Kevin; Douglas Mark

2012-01-01

The Flexible Array Concentrator Technology (FACT) is a lightweight, high-performance reflective concentrator blanket assembly that can be used on flexible solar array blankets. The FACT concentrator replaces every other row of solar cells on a solar array blanket, significantly reducing the cost of the array. The modular design is highly scalable for the array system designer, and exhibits compact stowage, good off-pointing acceptance, and mass/cost savings. The assembly s relatively low concentration ratio, accompanied by a large radiative area, provides for a low cell operating temperature, and eliminates many of the thermal problems inherent in high-concentration-ratio designs. Unlike other reflector technologies, the FACT concentrator modules function on both z-fold and rolled flexible solar array blankets, as well as rigid array systems. Mega-ROSA (Mega Roll-Out Solar Array) is a new, highly modularized and extremely scalable version of ROSA that provides immense power level range capability from 100 kW to several MW in size. Mega-ROSA will enable extremely high-power spacecraft and SEP-powered missions, including space-tug and largescale planetary science and lunar/asteroid exploration missions. Mega-ROSA's inherent broad power scalability is achieved while retaining ROSA s solar array performance metrics and missionenabling features for lightweight, compact stowage volume and affordability. This innovation will enable future ultra-high-power missions through lowcost (25 to 50% cost savings, depending on PV and blanket technology), lightweight, high specific power (greater than 200 to 400 Watts per kilogram BOL (beginning-of-life) at the wing level depending on PV and blanket technology), compact stowage volume (greater than 50 kilowatts per cubic meter for very large arrays), high reliability, platform simplicity (low failure modes), high deployed strength/stiffness when scaled to huge sizes, and high-voltage operation capability. Mega-ROSA is adaptable to all photovoltaic and concentrator flexible blanket technologies, and can readily accommodate standard multijunction and emerging ultra-lightweight IMM (inverted metamorphic) photovoltaic flexible blanket assemblies, as well as ENTECHs Stretched Lens Array (SLA) and DSSs (Deployable Space Systems) FACT, which allows for cost reduction at the array level.

Composite flexible blanket insulation

NASA Technical Reports Server (NTRS)

Kourtides, Demetrius A. (Inventor); Lowe, David M. (Inventor)

1994-01-01

An improved composite flexible blanket insulation is presented comprising top silicon carbide having an interlock design, wherein the reflective shield is composed of single or double aluminized polyimide and wherein the polyimide film has a honeycomb pattern.

Effect on the tritium breeding ratio for a distributed ICRF antenna in a DEMO reactor

NASA Astrophysics Data System (ADS)

Garcia, A.; Noterdaeme, J.-M.; Fischer, U.; Dies, J.

2015-12-01

The paper reports results of MCNP-5 calculations to assess the effect on the Tritium Breeding Ratio (TBR) when integrating a distributed Ion Cyclotron Range of Frequencies (ICRF) antenna in the blanket of DEMO fusion power reactor. The calculations consider different parameters such as the ICRF covering ratio and the type of breeding blanket including the Helium Cooled Pebble Bed (HCPB) and the Helium Cooled Lithium Lead (HCLL) concepts. For an antenna with a full toroidal circumference of 360°, located poloidally at 40° with a poloidal extension of 1 m, the reduction of the TBR is -0.349% for the HCPB blanket and -0.532% for the HCLL blanket. The distributed ICRF antenna is thus shown to have only a marginal effect on the TBR of the DEMO reactor.

Direct LiT Electrolysis in a Metallic Fusion Blanket

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

Olson, Luke

2016-09-30

A process that simplifies the extraction of tritium from molten lithium-based breeding blankets was developed. The process is based on the direct electrolysis of lithium tritide using a ceramic Li ion conductor that replaces the molten salt extraction step. Extraction of tritium in the form of lithium tritide in the blankets/targets of fusion/fission reactors is critical in order to maintain low concentrations. This is needed to decrease the potential tritium permeation to the surroundings and large releases from unforeseen accident scenarios. Extraction is complicated due to required low tritium concentration limits and because of the high affinity of tritium formore » the blanket. This work identified, developed and tested the use of ceramic lithium ion conductors capable of recovering hydrogen and deuterium through an electrolysis step at high temperatures.« less

Thermally distinct ejecta blankets from Martian craters

NASA Astrophysics Data System (ADS)

Betts, B. H.; Murray, B. C.

1993-06-01

A study of Martian ejecta blankets is carried out using the high-resolution thermal IR/visible data from the Termoskan instrument aboard Phobos '88 mission. It is found that approximately 100 craters within the Termoskan data have an ejecta blanket distinct in the thermal infrared (EDITH). These features are examined by (1) a systematic examination of all Termoskan data using high-resolution image processing; (2) a study of the systematics of the data by compiling and analyzing a data base consisting of geographic, geologic, and mormphologic parameters for a significant fraction of the EDITH and nearby non-EDITH; and (3) qualitative and quantitative analyses of localized regions of interest. It is noted that thermally distinct ejecta blankets are excellent locations for future landers and remote sensing because of relatively dust-free surface exposures of material excavated from depth.

Direct Lit Electrolysis In A Metallic Lithium Fusion Blanket

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

Colon-Mercado, H.; Babineau, D.; Elvington, M.

2015-10-13

A process that simplifies the extraction of tritium from molten lithium based breeding blankets was developed.  The process is based on the direct electrolysis of lithium tritide using a ceramic Li ion conductor that replaces the molten salt extraction step. Extraction of tritium in the form of lithium tritide in the blankets/targets of fission/fusion reactors is critical in order to maintained low concentrations.  This is needed to decrease the potential tritium permeation to the surroundings and large releases from unforeseen accident scenarios. Because of the high affinity of tritium for the blanket, extraction is complicated at the required low levels. This workmore » identified, developed and tested the use of ceramic lithium ion conductors capable of recovering the hydrogen and deuterium thru an electrolysis step at high temperatures. « less

Design, optimization, and analysis of a self-deploying PV tent array

NASA Astrophysics Data System (ADS)

Collozza, Anthony J.

1991-06-01

A tent shaped PV array was designed and the design was optimized for maximum specific power. In order to minimize output power variation a tent angle of 60 deg was chosen. Based on the chosen tent angle an array structure was designed. The design considerations were minimal deployment time, high reliability, and small stowage volume. To meet these considerations the array was chosen to be self-deployable, form a compact storage configuration, using a passive pressurized gas deployment mechanism. Each structural component of the design was analyzed to determine the size necessary to withstand the various forces to which it would be subjected. Through this analysis the component weights were determined. An optimization was performed to determine the array dimensions and blanket geometry which produce the maximum specific power for a given PV blanket. This optimization was performed for both lunar and Martian environmental conditions. Other factors such as PV blanket types, structural material, and wind velocity (for Mars array), were varied to determine what influence they had on the design point. The performance specifications for the array at both locations and with each type of PV blanket were determined. These specifications were calculated using the Arimid fiber composite as the structural material. The four PV blanket types considered were silicon, GaAs/Ge, GaAsCLEFT, and amorphous silicon. The specifications used for each blanket represented either present day or near term technology. For both the Moon and Mars the amorphous silicon arrays produced the highest specific power.

Map showing scenic features and recreation facilities of the Salina quadrangle, Utah

USGS Publications Warehouse

Williams, Paul L.; Covington, Harry R.

1973-01-01

This map is intended as a guide for those who enjoy outdoor recreation in magnificent scenic settings.The Salina quadrangle lies in the heart of the Colorado Plateau, a sparsely populated land of unique and outstanding scenic beauty. The eastern half of the quadrangle is a great desert, partly blanketed by sand dunes, but  mostly an area of badlands multicolored cliffs and benches of virtually barren rock, and deeply incised canyons. In the west half of the quadrangle, rugged tree-covered foothills flank high forested plateaus rimmed by cliffs. On these High Plateaus, dense coniferous forest is interspersed with wide grassy parks, grazed in summer by sheep and cattle. Valleys between the plateaus contain irrigated crop lands.

KSC-04PD-0435

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers attach an overhead crane to NASAs MESSENGER spacecraft. The spacecraft will be moved to a work stand where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-04PD-0434

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the high bay clean room at the Astrotech Space Operations processing facilities near KSC, workers prepare to attach an overhead crane to NASAs MESSENGER spacecraft. The spacecraft will be moved to a work stand where employees of the Johns Hopkins University Applied Physics Laboratory, builders of the spacecraft, will perform an initial state-of-health check. Then processing for launch can begin, including checkout of the power systems, communications systems and control systems. The thermal blankets will also be attached for flight. MESSENGER short for MErcury Surface, Space ENvironment, GEochemistry and Ranging will be launched May 11 on a six-year mission aboard a Boeing Delta II rocket. Liftoff is targeted for 2:26 a.m. EDT on Tuesday, May 11.

KSC-97PC1024

NASA Image and Video Library

1997-07-10

A Daimler-Benz Aerospace staff member installs thermal blanket insulation on the back cover of the Huygens probe in the Payload Hazardous Servicing Facility at KSC in July. Instruments mounted on the probe, which is owned by the European Space Agency (ESA), will receive atmospheric and surface data on Saturn’s main moon, Titan, to send back to Earth as part of the Cassini mission. The back cover, yet to be attached to the Cassini orbiter, will protect the probe during descent onto Titan. A four-year, close-up study of the Saturnian system, the mission is scheduled for launch from Cape Canaveral Air Station in October 1997. It will take seven years for the spacecraft to reach Saturn. Aerospatiale is the prime contractor for ESA

Chemical characterization of selected LDEF polymeric materials

NASA Technical Reports Server (NTRS)

Young, Philip R.; Slemp, Wayne S.

1991-01-01

Chemical characterization of selected polymeric materials which received exposure on the Long Duration Exposure Facility (LDEF) is reported. The specimens examined include silvered fluorinated ethylene propylene Teflon thermal blanket material, polysulfone, epoxy, polyimide matrix resin/graphite fiber reinforced composites, and several high performance polymer films. These specimens came from numerous LDEF locations, and thus received different environmental exposures. The results to date show no significant change at the molecular level in the polymer that survived exposure. Scanning electron and scanning tunneling microscopes show resin loss and a texturing of some specimens which resulted in a change in optical properties. The potential effect of a silicon-containing molecular contamination on these materials is addressed. The possibility of continued post-exposure degradation of some polymeric films is also proposed.

APT Blanket Thermal Analyses of Top Horizontal Row 1 Modules

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

Shadday, M.A.

1999-09-20

The Accelerator Production of Tritium (APT) cavity flood system (CFS) is designed to be the primary safeguard for the integrity of the blanket modules during loss of coolant accidents (LOCAs). For certain large break LOCAs the CFS also provides backup for the residual heat removal systems (RHRs) in cooling the target assemblies. In the unlikely event that the internal flow passages in a blanket module or target assembly dryout, decay heat in the metal structures will be dissipated to the CFS through the module or assembly walls (i.e., rung outer walls). The target assemblies consist of tungsten targets encased inmore » steel conduits, and they can safely sustain high metal temperatures. Under internally dry conditions, the cavity flood fluid will cool the target assemblies with vigorous nucleate boiling on the external surfaces. However, the metal structures in the blanket modules consist of lead cladded in aluminum, and they have a long-term exposure temperature limit currently set to 150 degrees C. Simultaneous LOCAs in both the target and blanket heat removal systems (HRS) could result in dryout of the target ladders, as well as the horizontal blanket modules above the target. The cavity flood coolant would boil on the outside surfaces of the target ladder rungs, and the resultant steam could reduce the effectiveness of convection heat transfer from the blanket modules to the cavity flood coolant. A two-part analysis was conducted to ascertain if the cavity flood system can adequately cool the blanket modules above the targets, even when boiling is occurring on the outer surfaces of the target ladder rungs. The first part of the analysis was to model transient thermal conduction in the front top horizontal row 1 module (i.e. top horizontal modules nearest the incoming beam), while varying parametrically the convection heat transfer coefficient (htc) for the external surfaces exposed to the cavity flood flow. This part of the analysis demonstrated that the module could adequately conduct heat to the outer module surfaces, given reasonable values for the convection heat transfer coefficients. The second part of the analysis consisted of two-phase flow modeling of the natural circulation of the cavity flood fluid past the top modules. Slots in the top shield allow the cavity flood fluid to circulate. The required width for these slots, to prevent steam from backing up and blanketing the outer surfaces of the top modules, was determined.« less

A high converter concept for fuel management with blanket fuel assemblies in boiling water reactors

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

Martinez-Frances, N.; Timm, W.; Rossbach, D.

2012-07-01

Studies on the natural Uranium saving and waste reduction potential of a multiple-plant BWR system were performed. The BWR High Converter system should enable a multiple recycling of MOX fuel in current BWR plants by introducing blanket fuel assemblies and burning Uranium and MOX fuel separately. The feasibility of Uranium cores with blankets and full-MOX cores with Plutonium qualities as low as 40% were studied. The power concentration due to blanket insertion is manageable with modern fuel and acceptable values for the thermal limits and reactivity coefficients were obtained. While challenges remain, full-MOX cores also complied with the main designmore » criteria. The combination of Uranium and Plutonium burners in appropriate proportions could enable obtaining as much as 40% more energy out of Uranium ore. Moreover, a proper adjustment of blanket average stay and Plutonium qualities could lead to a system with nearly no Plutonium left for final disposal. The achievement of such goals with current light water technology makes the BWR HC concept an attractive option to improve the fuel cycle until Gen-IV designs are mature. (authors)« less

Vibration and shape control of hinged light structures using electromagnetic forces

NASA Astrophysics Data System (ADS)

Matsuzaki, Yuji; Miyachi, Shigenobu; Sasaki, Toshiyuki

2003-08-01

This paper describes a new electromagnetic device for vibration control of a light-weighted deployable/retractable structure which consists of many small units connected with mechanical hinges. A typical example of such a structure is a solar cell paddle of an artificial satellite which is composed of many thin flexible blankets connected in series. Vibration and shape control of the paddle is not easy, because control force and energy do not transmit well between the blankets which are discretely connected by hinges with each other. The new device consists of a permanent magnet glued along an edge of a blanket and an electric current-conducting coil glued along an adjoining edge of another adjacent blanket. Conduction of the electric current in a magnetic field from the magnet generates an electromagnetic force on the coil. By changing the current in the coil, therefore, we may control the vibration and shape of the blankets. To confirm the effectiveness of the new device, constructing a simple paddle model consisting eight hinge- panels, we have carried out a model experiment of vibration and shape control of the paddle. In addition, a numerical simulation of vibration control of the hinge structure is performed to compare with measured data.

SEAL Studies of Variant Blanket Concepts and Materials

NASA Astrophysics Data System (ADS)

Cook, I.; Taylor, N. P.; Forty, C. B. A.; Han, W. E.

1997-09-01

Within the European SEAL ( Safety and Environmental Assessment of fusion power, Long-term) program, safety and environmental assessments have been performed which extend the results of the earlier SEAFP (Safety and Environmental Assessment of Fusion Power) program to a wider range of blanket designs and material choices. The four blanket designs analysed were those which had been developed within the Blanket program of the European Fusion Programme. All four are based on martensitic steel as structural material, and otherwise may be summarized as: water-cooled lithium-lead; dual-cooled lithium-lead; helium-cooled lithium silicate (BOT geometry); helium-cooled lithium aluminate (or zirconate) (BIT geometry). The results reveal that all the blankets show the favorable S&E characteristics of fusion, though there are interesting and significant differences between them. The key results are described. Assessments have also been performed of a wider range of materials than was considered in SEAFP. These were: an alternative vanadium alloy, an alternative low-activation martensitic steel, titanium-aluminum intermetallic, and SiC composite. Assessed impurities were included in the compositions, and these had very important effects upon some of the results. Key results impacting upon accident characteristics, recycling, and waste management are described.

Structural heat pipe. [for spacecraft wall thermal insulation system

NASA Technical Reports Server (NTRS)

Ollendorf, S. (Inventor)

1974-01-01

A combined structural reinforcing element and heat transfer member is disclosed for placement between a structural wall and an outer insulation blanket. The element comprises a heat pipe, one side of which supports the outer insulation blanket, the opposite side of which is connected to the structural wall. Heat penetrating through the outer insulation blanket directly reaches the heat pipe and is drawn off, thereby reducing thermal gradients in the structural wall. The element, due to its attachment to the structural wall, further functions as a reinforcing member.

APT Blanket System Loss-of-Coolant Accident (LOCA) Based on Initial Conceptual Design - Case 2: with Beam Shutdown Only

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

Hamm, L.L.

1998-10-07

This report is one of a series of reports that document normal operation and accident simulations for the Accelerator Production of Tritium (APT) blanket heat removal system. These simulations were performed for the Preliminary Safety Analysis Report. This report documents the results of simulations of a Loss-of-Flow Accident (LOFA) where power is lost to all of the pumps that circulate water in the blanket region, the accelerator beam is shut off and neither the residual heat removal nor cavity flood systems operate.

Advanced Development Waste Processing Unit for Combat Vehicles. Phase 2

DTIC Science & Technology

1987-12-29

Johns Manville Manufacturers # : 5346474 Type: Cera Blanket Size: 6 lb., I" thick Amount Used: 24" x 48" total TIME RPM TI O T 2 F T ,F T 4, Tbient F 1200...WPUBMO01 DATA SHEET DSO01-4 Date:NOV 2 5 186 i~ L , Candidate Insulation: Manufacturer: Johns Manville Manufacturer’s # : 5346474. Type: Cera Blanket Size...SHEET DS001-5 Date: EC 0 3 186 Candidate Insulation: Manufacturer: Johns Manville Manufacturerls # : 5346474 Type: Cera Blanket (F Size: 6 lb., 1

Design of the helium cooled lithium lead breeding blanket in CEA: from TBM to DEMO

NASA Astrophysics Data System (ADS)

Aiello, G.; Aubert, J.; Forest, L.; Jaboulay, J.-C.; Li Puma, A.; Boccaccini, L. V.

2017-04-01

The helium cooled lithium lead (HCLL) blanket concept was originally developed in CEA at the beginning of 2000: it is one of the two European blanket concepts to be tested in ITER in the form of a test blanket module (TBM) and one of the four blanket concepts currently being considered for the DEMOnstration reactor that will follow ITER. The TBM is a highly optimized component for the ITER environment that will provide crucial information for the development of the DEMO blanket, but its design needs to be adapted to the DEMO reactor. With respect to the TBM design, reduction of the steel content in the breeding zone (BZ) is sought in order to maximize tritium breeding reactions. Different options are being studied, with the potential of reaching tritium breeding ratio (TBR) values up to 1.21. At the same time, the design of the back supporting structure (BSS), which is a DEMO specific component that has to support the blanket modules inside the vacuum vessel (VV), is ongoing with the aim of maximizing the shielding power and minimizing pumping power. This implies a re-engineering of the modules’ attachment system. Design changes however, will have an impact on the manufacturing and assembly sequences that are being developed for the HCLL-TBM. Due to the differences in joint configurations, thicknesses to be welded, heat dissipation and the various technical constraints related to the accessibility of the welding tools and implementation of non-destructive examination (NDE), the manufacturing procedure should be adapted and optimized for DEMO design. Laser welding instead of TIG could be an option to reduce distortions. The time-of-flight diffraction (TOFD) technique is being investigated for NDE. Finally, essential information expected from the HCLL-TBM program that will be needed to finalize the DEMO design is discussed.

2014 Strategic Sustainability Performance Plan

DTIC Science & Technology

2014-06-30

Strategic Sourcing Initiatives, such as Blanket Purchase Agreements ( BPAs ) for office products and imaging equipment, which include sustainable...end of FY2014. Use Federal Strategic Sourcing Initiatives, such as Blanket Purchase Agreements ( BPAs ) Yes USACE is required to participate in

Enhanced fuel production in thorium/lithium hybrid blankets utilizing uranium multipliers

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

Pitulski, R.H.

1979-10-01

A consistent neutronics analysis is performed to determine the effectiveness of uranium bearing neutron multiplier zones on increasing the production of U/sup 233/ in thorium/lithium blankets for use in a tokamak fusion-fission hybrid reactor. The nuclear performance of these blankets is evaluated as a function of zone thicknesses and exposure by using the coupled transport burnup code ANISN-CINDER-HIC. Various parameters such as U/sup 233/, Pu/sup 239/, and H/sup 3/ production rates, the blanket energy multiplication, isotopic composition of the fuels, and neutron leakages into the various zones are evaluated during a 5 year (6 MW.y.m/sup -2/) exposure period. Although themore » results of this study were obtained for a tokomak magnetic fusion device, the qualitative behavior associated with the use of the uranium bearing neutron multiplier should be applicable to all fusion-fission hybrids.« less

Stacbeam 2

NASA Astrophysics Data System (ADS)

Adams, L. R.; Vonroos, A.

1985-04-01

An investigation being conducted by Astro Aerospace Corporation (Astro) for Jet Propulsion Laboratory in which efficient structures for geosynchronous spacecraft solar arrays are being developed is discussed. Recent developments in solar blanket technology, including the introduction of ultrathin (50 micrometer) silicon solar cells with conversion efficiencies approaching 15 percent, have resulted in a significant increase in blanket specific power. System specific power depends not only on blanket mass but also on the masses of the support structure and deployment mechanism. These masses must clearly be reduced, not only to minimize launch weight, but also to increase array natural frequency. The solar array system natural frequency should be kept high in order to reduce the demands on the attitude control system. This goal is approached by decreasing system mass, by increasing structural stiffness, and by partitioning the blanket. As a result of this work, a highly efficient structure for deploying a solar array was developed.

Effect on the tritium breeding ratio for a distributed ICRF antenna in a DEMO reactor

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

Garcia, A., E-mail: albert.garcia.hp@gmail.com; Karlsruhe Institute of Technology; Polytechnic University of Catalonia

The paper reports results of MCNP-5 calculations to assess the effect on the Tritium Breeding Ratio (TBR) when integrating a distributed Ion Cyclotron Range of Frequencies (ICRF) antenna in the blanket of DEMO fusion power reactor. The calculations consider different parameters such as the ICRF covering ratio and the type of breeding blanket including the Helium Cooled Pebble Bed (HCPB) and the Helium Cooled Lithium Lead (HCLL) concepts. For an antenna with a full toroidal circumference of 360°, located poloidally at 40° with a poloidal extension of 1 m, the reduction of the TBR is −0.349% for the HCPB blanket andmore » −0.532% for the HCLL blanket. The distributed ICRF antenna is thus shown to have only a marginal effect on the TBR of the DEMO reactor.« less

Neutronics Analysis of Water-Cooled Ceramic Breeder Blanket for CFETR

NASA Astrophysics Data System (ADS)

Zhu, Qingjun; Li, Jia; Liu, Songlin

2016-07-01

In order to investigate the nuclear response to the water-cooled ceramic breeder blanket models for CFETR, a detailed 3D neutronics model with 22.5° torus sector was developed based on the integrated geometry of CFETR, including heterogeneous WCCB blanket models, shield, divertor, vacuum vessel, toroidal and poloidal magnets, and ports. Using the Monte Carlo N-Particle Transport Code MCNP5 and IAEA Fusion Evaluated Nuclear Data Library FENDL2.1, the neutronics analyses were performed. The neutron wall loading, tritium breeding ratio, the nuclear heating, neutron-induced atomic displacement damage, and gas production were determined. The results indicate that the global TBR of no less than 1.2 will be a big challenge for the water-cooled ceramic breeder blanket for CFETR. supported by the National Magnetic Confinement Fusion Science Program of China (Nos. 2013GB108004, 2014GB122000, and 2014GB119000), and National Natural Science Foundation of China (No. 11175207)

A photovoltaic catenary-tent array for the Martian surface

NASA Technical Reports Server (NTRS)

Crutchik, M.; Colozza, Anthony J.; Appelbaum, J.

1993-01-01

To provide electrical power during an exploration mission to Mars, a deployable tent-shaped structure with a flexible photovoltaic (PV) blanket is proposed. The array is designed with a self-deploying mechanism utilizing pressurized gas expansion. The structural design for the array uses a combination of cables, beams, and columns to support and deploy the PV blanket. Under the force of gravity a cable carrying a uniform load will take the shape of a catenary curve. A catenary-tent collector is self shadowing which must be taken into account in the solar radiation calculation. The shape and the area of the shadow on the array was calculated and used in the determination of the global radiation on the array. The PV blanket shape and structure dimension were optimized to achieve a configuration which maximizes the specific power (W/kg). The optimization was performed for four types of PV blankets (Si, GaAs/Ge, GaAs CLEFT, and amorphous Si) and four types of structure materials (Carbon composite, Aramid Fiber composite, Aluminum, and Magnesium). The results show that the catenary shape of the PV blanket, which produces the highest specific power, corresponds to zero end angle at the base with respect to the horizontal. The tent angle is determined by the combined effect of the array structure specific mass and the PV blanket output power. The combination of carbon composite structural material and GaAs CLEFT solar cells produce the highest specific power. The study was carried out for two sites on Mars corresponding to the Viking Lander locations. The designs were also compared for summer, winter, and yearly operation.

Heat barrier for use in a nuclear reactor facility

DOEpatents

Keegan, Charles P.

1988-01-01

A thermal barrier for use in a nuclear reactor facility is disclosed herein. Generally, the thermal barrier comprises a flexible, heat-resistant web mounted over the annular space between the reactor vessel and the guard vessel in order to prevent convection currents generated in the nitrogen atmosphere in this space from entering the relatively cooler atmosphere of the reactor cavity which surrounds these vessels. Preferably, the flexible web includes a blanket of heat-insulating material formed from fibers of a refractory material, such as alumina and silica, sandwiched between a heat-resistant, metallic cloth made from stainless steel wire. In use, the web is mounted between the upper edges of the guard vessel and the flange of a sealing ring which surrounds the reactor vessel with a sufficient enough slack to avoid being pulled taut as a result of thermal differential expansion between the two vessels. The flexible web replaces the rigid and relatively complicated structures employed in the prior art for insulating the reactor cavity from the convection currents generated between the reactor vessel and the guard vessel.

KSC-04pd1839

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - From left, Martin Wilson, manager of Thermal Protection System (TPS) operations for United Space Alliance, briefs NASA Administrator Sean O’Keefe, KSC Director of the Spaceport Services Scott Kerr, NASA Associate Administrator of the Space Operations Mission Directorate William Readdy, and Center Director James Kennedy (right) on the temporary tile shop set up in the RLV hangar. O’Keefe and Readdy are visiting KSC to survey the damage sustained by KSC facilities from Hurricane Frances. The Thermal Protection System Facility (TPSF), which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof in the storm, which blew across Central Florida Sept. 4-5. Undamaged equipment was removed from the TPSF and stored in the hangar. NASA’s three Space Shuttle orbiters -- Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft, awaiting launch in October, were well protected and unharmed.

Geology of Southern Quintana Roo (Mexico) and the Chicxulub Ejecta Blanket

NASA Astrophysics Data System (ADS)

Schönian, F.; Tagle, R.; Stöffler, D.; Kenkmann, T.

2005-03-01

In southern Quintana Roo (Mexico) the Chicxulub ejecta blanket is discontinuously filling a karstified pre-KT land surface. This suggests a completely new scenario for the geological evolution of the southern Yucatán Peninsula.

Self-deploying photovoltaic power system

NASA Technical Reports Server (NTRS)

Colozza, Anthony J. (Inventor)

1993-01-01

A lightweight flexible photovoltaic (PV) blanket is attached to a support structure of initially stowed telescoping members. The deployment mechanism comprises a series of extendable and rotatable columns. As these columns are extended the PV blanket is deployed to its proper configuration.

76 FR 48855 - Questar Pipeline Company; Notice of Request Under Blanket Authorization

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-09

... gas to be stored at its Clay Basin storage reservoir and increase the maximum certificated shut-in pressure of Clay Basin located in Daggett County, Utah. The request was made pursuant to the blanket...

Advanced Burner Reactor with Breed-and-Burn Thorium Blankets for Improved Economics and Resource Utilization

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

Greenspan, Ehud

2015-11-04

This study assesses the feasibility of designing Seed and Blanket (S&B) Sodium-cooled Fast Reactor (SFR) to generate a significant fraction of the core power from radial thorium fueled blankets that operate on the Breed-and-Burn (B&B) mode without exceeding the radiation damage constraint of presently verified cladding materials. The S&B core is designed to maximize the fraction of neutrons that radially leak from the seed (or “driver”) into the subcritical blanket and reduce neutron loss via axial leakage. The blanket in the S&B core makes beneficial use of the leaking neutrons for improved economics and resource utilization. A specific objective ofmore » this study is to maximize the fraction of core power that can be generated by the blanket without violating the thermal hydraulic and material constraints. Since the blanket fuel requires no reprocessing along with remote fuel fabrication, a larger fraction of power from the blanket will result in a smaller fuel recycling capacity and lower fuel cycle cost per unit of electricity generated. A unique synergism is found between a low conversion ratio (CR) seed and a B&B blanket fueled by thorium. Among several benefits, this synergism enables the very low leakage S&B cores to have small positive coolant voiding reactivity coefficient and large enough negative Doppler coefficient even when using inert matrix fuel for the seed. The benefits of this synergism are maximized when using an annular seed surrounded by an inner and outer thorium blankets. Among the high-performance S&B cores designed to benefit from this unique synergism are: (1) the ultra-long cycle core that features a cycle length of ~7 years; (2) the high-transmutation rate core where the seed fuel features a TRU CR of 0.0. Its TRU transmutation rate is comparable to that of the reference Advanced Burner Reactor (ABR) with CR of 0.5 and the thorium blanket can generate close to 60% of the core power; but requires only one sixth of the reprocessing and fabrication capacity per unit of core power. Nevertheless, these high-performance cores were designed to set upper bounds on the S&B core performance by using larger height and pressure drop than those of typical SFR design. A study was subsequently undertaken to quantify the tradeoff between S&B core design variables and the core performance. This study concludes that a viable S&B core can be designed without significant deviation from SFR core design practices. For example, the S&B core with 120cm active height will be comparable in volume, HM mass and specific power with the S-PRISM core and could fit within the S-PRISM reactor vessel. 43% of this core power will be generated by the once-through thorium blanket; the required capacity for reprocessing and remote fuel fabrication per unit of electricity generated will be approximately one fifth of that for a comparable ABR. The sodium void worth of this 120cm tall S&B core is significantly less positive than that of the reference ABR and the Doppler coefficient is only slightly smaller even though the seed uses a fertile-free fuel. The seed in the high transmutation core requires inert matrix fuel (TRU-40Zr) that has been successfully irradiated by the Fuel Cycle Research & Development program. An additional sensitivity analysis was later conducted to remove the bias introduced by the discrepancy between radiation damage constraints -- 200 DPA applied for S&B cores and fast fluence of 4x1023 n(>0.1MeV)/cm2 applied for ABR core design. Although the performance characteristics of the S&B cores are sensitive to the radiation damage constraint applied, the S&B cores offer very significant performance improvements relative to the conventional ABR core design when using identical constraint.« less

Water-Repellency Probe

NASA Technical Reports Server (NTRS)

Rosen, Charles D.; Mitchell, Shirley M.; Jolly, Stanley R.; Jackson, Richard G.; Fleming, Scott T.; Roberts, William J.; Bell, Daniel R., III

1996-01-01

Instrument yielding presence or absence of waterproofing agent at any given depth in blanket developed. In original application, blankets in question part of space shuttle thermal protection system. Instrument utilized to determine extent of waterproofing "burnout" due to re-entry heating and adverse environment exposure.

What are the Effects of Protest Fear?

DTIC Science & Technology

2014-06-01

Program AT&L Acquisition, Technology, and Logistics BPA blanket purchase agreement CONUS continental United States COR...they have awarded a task/delivery order against an IDIQ contract (or Blanket Purchase Agreement [ BPA ]) in order to avoid a bid protest. The data shows

Lightweight IMM PV Flexible Blanket Assembly

NASA Technical Reports Server (NTRS)

Spence, Brian

2015-01-01

Deployable Space Systems (DSS) has developed an inverted metamorphic multijunction (IMM) photovoltaic (PV) integrated modular blanket assembly (IMBA) that can be rolled or z-folded. This IMM PV IMBA technology enables a revolutionary flexible PV blanket assembly that provides high specific power, exceptional stowed packaging efficiency, and high-voltage operation capability. DSS's technology also accommodates standard third-generation triple junction (ZTJ) PV device technologies to provide significantly improved performance over the current state of the art. This SBIR project demonstrated prototype, flight-like IMM PV IMBA panel assemblies specifically developed, designed, and optimized for NASA's high-voltage solar array missions.

Automated Laser Cutting In Three Dimensions

NASA Technical Reports Server (NTRS)

Bird, Lisa T.; Yvanovich, Mark A.; Angell, Terry R.; Bishop, Patricia J.; Dai, Weimin; Dobbs, Robert D.; He, Mingli; Minardi, Antonio; Shelton, Bret A.

1995-01-01

Computer-controlled machine-tool system uses laser beam assisted by directed flow of air to cut refractory materials into complex three-dimensional shapes. Velocity, position, and angle of cut varied. In original application, materials in question were thermally insulating thick blankets and tiles used on space shuttle. System shapes tile to concave or convex contours and cuts beveled edges on blanket, without cutting through outer layer of quartz fabric part of blanket. For safety, system entirely enclosed to prevent escape of laser energy. No dust generated during cutting operation - all material vaporized; larger solid chips dislodged from workpiece easily removed later.

Olivas participating in EVA during Expedition/STS-117 Joint Operations

NASA Image and Video Library

2007-06-15

ISS015-E-12943 (15 June 2007) --- Anchored to a foot restraint on Space Shuttle Atlantis' remote manipulator system (RMS) robotic arm, astronaut John "Danny" Olivas, STS-117 mission specialist, repairs a 4-by-6-inch section of a thermal blanket on Atlantis' port orbital maneuvering system (OMS) pod that was damaged during the shuttle's climb to orbit last week. During the repair, Olivas pushed the turned up portion of the thermal blanket back into position, used a medical stapler to secure the layers of the blanket, and pinned it in place against adjacent thermal tile.

Olivas participating in EVA during Expedition/STS-117 Joint Operations

NASA Image and Video Library

2007-06-15

ISS015-E-12952 (15 June 2007) --- Anchored to a foot restraint on Space Shuttle Atlantis' remote manipulator system (RMS) robotic arm, astronaut John "Danny" Olivas, STS-117 mission specialist, repairs a 4-by-6-inch section of a thermal blanket on Atlantis' port orbital maneuvering system (OMS) pod that was damaged during the shuttle's climb to orbit last week. During the repair, Olivas pushed the turned up portion of the thermal blanket back into position, used a medical stapler to secure the layers of the blanket, and pinned it in place against adjacent thermal tile.

Experimental investigation of MHD pressure losses in a mock-up of a liquid metal blanket

NASA Astrophysics Data System (ADS)

Mistrangelo, C.; Bühler, L.; Brinkmann, H.-J.

2018-03-01

Experiments have been performed to investigate the influence of a magnetic field on liquid metal flows in a scaled mock-up of a helium cooled lead lithium (HCLL) blanket. During the experiments pressure differences between points on the mock-up have been recorded for various values of flow rate and magnitude of the imposed magnetic field. The main contributions to the total pressure drop in the test-section have been identified as a function of characteristic flow parameters. For sufficiently strong magnetic fields the non-dimensional pressure losses are practically independent on the flow rate, namely inertia forces become negligible. Previous experiments on MHD flows in a simplified test-section for a HCLL blanket showed that the main contributions to the total pressure drop in a blanket module originate from the flow in the distributing and collecting manifolds. The new experiments confirm that the largest pressure drops occur along manifolds and near the first wall of the blanket module, where the liquid metal passes through small openings in the stiffening plates separating two breeder units. Moreover, the experimental data shows that with the present manifold design the flow does not distribute homogeneously among the 8 stacked boxes that form the breeding zone.

Clinical outcome comparison of immediate blanket treatment versus a delayed pathogen-based treatment protocol for clinical mastitis in a New York dairy herd.

PubMed

Vasquez, A K; Nydam, D V; Capel, M B; Eicker, S; Virkler, P D

2017-04-01

The purpose was to compare immediate intramammary antimicrobial treatment of all cases of clinical mastitis with a selective treatment protocol based on 24-h culture results. The study was conducted at a 3,500-cow commercial farm in New York. Using a randomized design, mild to moderate clinical mastitis cases were assigned to either the blanket therapy or pathogen-based therapy group. Cows in the blanket therapy group received immediate on-label intramammary treatment with ceftiofur hydrochloride for 5 d. Upon receipt of 24 h culture results, cows in the pathogen-based group followed a protocol automatically assigned via Dairy Comp 305 (Valley Agricultural Software, Tulare, CA): Staphylococcus spp., Streptococcus spp., or Enterococcus spp. were administered on-label intramammary treatment with cephapirin sodium for 1 d. Others, including cows with no-growth or gram-negative results, received no treatment. A total of 725 cases of clinical mastitis were observed; 114 cows were not enrolled due to severity. An additional 122 cases did not meet inclusion criteria. Distribution of treatments for the 489 qualifying events was equal between groups (pathogen-based, n = 246; blanket, n = 243). The proportions of cases assigned to the blanket and pathogen-based groups that received intramammary therapy were 100 and 32%, respectively. No significant differences existed between blanket therapy and pathogen-based therapy in days to clinical cure; means were 4.8 and 4.5 d, respectively. The difference in post-event milk production between groups was not statistically significant (blanket therapy = 34.7 kg; pathogen-based = 35.4 kg). No differences were observed in test-day linear scores between groups; least squares means of linear scores was 4.3 for pathogen-based cows and 4.2 for blanket therapy cows. Odds of survival 30 d postenrollment was similar between groups (odds ratio of pathogen-based = 1.6; 95% confidence interval: 0.7-3.7) as was odds of survival to 60 d (odds ratio = 1.4; 95% confidence interval: 0.7-2.6). The one significant difference found for the effect of treatment was in hospital days; pathogen-based cows experienced, on average, 3 fewer days than blanket therapy cows. A majority (68.5%) of moderate and mild clinical cases would not have been treated if all cows on this trial were enrolled in a pathogen-based protocol. The use of a strategic treatment protocol based on 24-h postmastitis pathogen results has potential to efficiently reduce antimicrobial use. Copyright © 2017 American Dairy Science Association. Published by Elsevier Inc. All rights reserved.

KSC-04pd1840

NASA Image and Video Library

2004-09-18

KENNEDY SPACE CENTER, FLA. - Martin Wilson (second from right), manager of Thermal Protection System (TPS) operations for United Space Alliance (USA) , introduces Kevin Harrington, manager of Soft Goods Production in the TPSF, during a briefing to (from left) NASA Administrator Sean O’Keefe, KSC Director of Shuttle Processing Michael E. Wetmore, Center Director James Kennedy and KSC Director of the Spaceport Services Scott Kerr (behind Kennedy), on the temporary tile shop set up in the RLV hangar. O’Keefe and NASA Associate Administrator of Space Operations Mission Directorate William Readdy are visiting KSC to survey the damage sustained by KSC facilities from Hurricane Frances. The Thermal Protection System Facility (TPSF), which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof in the storm, which blew across Central Florida Sept. 4-5. The Labor Day storm also caused significant damage to the Vehicle Assembly Building and Processing Control Center. Additionally, the Operations and Checkout Building, Vertical Processing Facility, Hangar AE, Hangar S and Hangar AF Small Parts Facility each received substantial damage. Undamaged equipment was removed from the TPSF and stored in the hangar. However, well-protected and unharmed were NASA’s three Space Shuttle orbiters -- Discovery, Atlantis and Endeavour - along with the Shuttle launch pads, all of the critical flight hardware for the orbiters and the International Space Station, and NASA’s Swift spacecraft that is awaiting launch in October.

Final Technical Report for "Nuclear Technologies for Near Term Fusion Devices"

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

Wilson, Paul P.H.; Sawan, Mohamed E.; Davis, Andrew

Over approximately 18 years, this project evolved to focus on a number of related topics, all tied to the nuclear analysis of fusion energy systems. For the earliest years, the University of Wisconsin (UW)’s effort was in support of the Advanced Power Extraction (APEX) study to investigate high power density first wall and blanket systems. A variety of design concepts were studied before this study gave way to a design effort for a US Test Blanket Module (TBM) to be installed in ITER. Simultaneous to this TBM project, nuclear analysis supported the conceptual design of a number of fusion nuclearmore » science facilities that might fill a role in the path to fusion energy. Beginning in approximately 2005, this project added a component focused on the development of novel radiation transport software capability in support of the above nuclear analysis needs. Specifically, a clear need was identified to support neutron and photon transport on the complex geometries associated with Computer-Aided Design (CAD). Following the initial development of the Direct Accelerated Geoemtry Monte Carlo (DAGMC) capability, additional features were added, including unstructured mesh tallies and multi-physics analysis such as the Rigorous 2-Step (R2S) methodology for Shutdown Dose Rate (SDR) prediction. Throughout the project, there were also smaller tasks in support of the fusion materials community and for the testing of changes to the nuclear data that is fundamental to this kind of nuclear analysis.« less

Tritium assay of Li sub 2 O pellets in the LBM/LOTUS experiments

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

Quanci, J.; Azam, S.; Bertone, P.

1986-01-01

One of the objectives of the Lithium Blanket Module (LBM) program is to test the ability of advanced neutronics codes to model the tritium breeding characteristics of a fusion blanket exposed to a toroidal fusion neutron source. The LBM consists of over 20,000 cylindrical lithium oxide pellets and numerous diagnostic pellets and wafers. The LBM has been irradiated at the Ecole Polytechnique Federale de Lausanne (EPFL) LOTUS facility with a Haefely sealed neutron generator that gives a point deuterium-tritium neutron source up to 5 {times} 10{sup 12} 14-MeV n/s. Both Princeton Plasma Physics Laboratory (PPL) and EPFL assayed the tritiummore » bred at various positions in the LBM. EPFL employed a dissolution technique while PPL recovered the tritium by a thermal extraction method. EPFL uses 0.38-g, 75% TD, lithium oxide diagnostic wafers to evaluate the tritium bred in the LBM. PPPL employs a thermal extraction method to determine the tritium bred in lithium oxide samples. In the initial experiments, diagnostic pellets and wafers were placed at five locations in the LBM central removable test rod at distances of 3, 9, 21, 36, and 48 cm from the front face of the module. The two sets of data for the tritium bred in the LBM along its centerline as a function of distance from the front face of the module were compared with each other, and with the predictions of two-dimensional neutronics codes. 1 ref.« less

Evaluation of erosion control blanket properties and test criteria for specification and design : final report.

DOT National Transportation Integrated Search

2016-07-01

A research project to investigate the product approval, design process, and ongoing product evaluation of erosion control blankets : (ECBs) for the Missouri Department of Transportation (MoDOT) was conducted. An overview of federal and state environm...

Thermal-hydraulic analysis of low activity fusion blanket designs

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

Fillo, J A; Powell, J; Yu, W S

1977-01-01

The heat transfer aspects of fusion blankets are considered where: (a) conduction and (b) boiling and condensation are the dominant heat transfer mechanisms. In some cases, unique heat transfer problems arise and additional heat transfer data and analyses may be required.

What are the Effects of Protest Fear?

DTIC Science & Technology

2014-06-17

Acquisition Professional Development Program AT&L Acquisition, Technology, and Logistics BPA blanket purchase agreement CONUS continental United States...Blanket Purchase Agreement [ BPA ]) in order to avoid a bid protest. The data shows that 88 respondents had done so throughout their career with 4,139

Warm Ocean Temperatures Blanket the Far-Western Pacific

NASA Image and Video Library

2001-03-28

Data taken during a 10-day collection cycle ending March 9, 2001, show that above-normal sea-surface heights and warmer ocean temp. red and white areas still blanket the far-western tropical Pacific and much of the north and south mid-Pacific.

RELAP5 Model of the First Wall/Blanket Primary Heat Transfer System

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

Popov, Emilian L; Yoder Jr, Graydon L; Kim, Seokho H

2010-06-01

ITER inductive power operation is modeled and simulated using a system level computer code to evaluate the behavior of the Primary Heat Transfer System (PHTS) and predict parameter operational ranges. The control algorithm strategy and derivation are summarized in this report as well. A major feature of ITER is pulsed operation. The plasma does not burn continuously, but the power is pulsed with large periods of zero power between pulses. This feature requires active temperature control to maintain a constant blanket inlet temperature and requires accommodation of coolant thermal expansion during the pulse. In view of the transient nature ofmore » the power (plasma) operation state a transient system thermal-hydraulics code was selected: RELAP5. The code has a well-documented history for nuclear reactor transient analyses, it has been benchmarked against numerous experiments, and a large user database of commonly accepted modeling practices exists. The process of heat deposition and transfer in the blanket modules is multi-dimensional and cannot be accurately captured by a one-dimensional code such as RELAP5. To resolve this, a separate CFD calculation of blanket thermal power evolution was performed using the 3-D SC/Tetra thermofluid code. A 1D-3D co-simulation more realistically models FW/blanket internal time-dependent thermal inertia while eliminating uncertainties in the time constant assumed in a 1-D system code. Blanket water outlet temperature and heat release histories for any given ITER pulse operation scenario are calculated. These results provide the basis for developing time dependent power forcing functions which are used as input in the RELAP5 calculations.« less

Discovering collectively informative descriptors from high-throughput experiments

PubMed Central

2009-01-01

Background Improvements in high-throughput technology and its increasing use have led to the generation of many highly complex datasets that often address similar biological questions. Combining information from these studies can increase the reliability and generalizability of results and also yield new insights that guide future research. Results This paper describes a novel algorithm called BLANKET for symmetric analysis of two experiments that assess informativeness of descriptors. The experiments are required to be related only in that their descriptor sets intersect substantially and their definitions of case and control are consistent. From resulting lists of n descriptors ranked by informativeness, BLANKET determines shortlists of descriptors from each experiment, generally of different lengths p and q. For any pair of shortlists, four numbers are evident: the number of descriptors appearing in both shortlists, in exactly one shortlist, or in neither shortlist. From the associated contingency table, BLANKET computes Right Fisher Exact Test (RFET) values used as scores over a plane of possible pairs of shortlist lengths [1,2]. BLANKET then chooses a pair or pairs with RFET score less than a threshold; the threshold depends upon n and shortlist length limits and represents a quality of intersection achieved by less than 5% of random lists. Conclusions Researchers seek within a universe of descriptors some minimal subset that collectively and efficiently predicts experimental outcomes. Ideally, any smaller subset should be insufficient for reliable prediction and any larger subset should have little additional accuracy. As a method, BLANKET is easy to conceptualize and presents only moderate computational complexity. Many existing databases could be mined using BLANKET to suggest optimal sets of predictive descriptors. PMID:20021653

Checkerboard seed-blanket thorium fuel core concepts for heavy water moderated reactors

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

Bromley, B.P.; Hyland, B.

2013-07-01

New reactor concepts to implement thorium-based fuel cycles have been explored to achieve maximum resource utilization. Pressure tube heavy water reactors (PT-HWR) are highly advantageous for implementing the use of thorium-based fuels because of their high neutron economy and on-line re-fuelling capability. The use of heterogeneous seed-blanket core concepts in a PT-HWR where higher-fissile-content seed fuel bundles are physically separate from lower-fissile-content blanket bundles allows more flexibility and control in fuel management to maximize the fissile utilization and conversion of fertile fuel. The lattice concept chosen was a 35-element bundle made with a homogeneous mixture of reactor grade Pu (aboutmore » 67 wt% fissile) and Th, and with a central zirconia rod to help reduce coolant void reactivity. Several checkerboard heterogeneous seed-blanket core concepts with plutonium-thorium-based fuels in a 700-MWe-class PT-HWR were analyzed, using a once-through thorium (OTT) cycle. Different combinations of seed and blanket fuel were tested to determine the impact on core-average burnup, fissile utilization, power distributions, and other performance parameters. It was found that various checkerboard core concepts can achieve a fissile utilization that is up to 26% higher than that achieved in a PT-HWR using more conventional natural uranium fuel bundles. Up to 60% of the Pu is consumed; up to 43% of the energy is produced from thorium, and up to 303 kg/year of Pa-233/U-233/U-235 are produced. Checkerboard cores with about 50% of low-power blanket bundles may require power de-rating (65% to 74%) to avoid exceeding maximum limits for channel and bundle powers and linear element ratings. (authors)« less

KSC-04PD-1777

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. United Space Alliance workers Dallas Lewis (left) and Damon Petty carry out equipment from the Thermal Protection System Facility (TPSF). The TPSF, which creates the TPS tiles, blankets and all the internal thermal control systems for the Space Shuttles, is almost totally unserviceable at this time after losing approximately 35 percent of its roof due to Hurricane Frances, which blew across Central Florida Sept. 4-5. Undamaged equipment is being moved to the RLV hangar at KSC. The maximum wind at the surface from Hurricane Frances was 94 mph from the northeast at 6:40 a.m. on Sunday, September 5. It was recorded at a weather tower located on the east shore of the Mosquito Lagoon near the Cape Canaveral National Seashore. The highest sustained wind at KSC was 68 mph.

KSC-05pd2530

NASA Image and Video Library

2005-11-30

KENNEDY SPACE CENTER, FLA. - In Orbiter Processing Facility Bay 2, the nose cap of space shuttle Endeavour is prepared for installation of thermal protection system blankets. Endeavour recently came out of a nearly two-year Orbiter Major Modification period which began in December 2003. Engineers and technicians spent 900,000 hours performing 124 modifications to the vehicle. These included all recommended return-to-flight safety modifications, bonding more than 1,000 thermal protection system tiles and inspecting more than 150 miles of wiring throughout the orbiter. Shuttle major modification periods are scheduled at regular intervals to enhance safety and performance, infuse new technology, and allow for thorough inspections of the airframe and wiring of the vehicles. This was the second of these modification periods performed entirely at Kennedy Space Center. Endeavour's previous modification was completed in March 1997.

KSC-01pp1730

NASA Image and Video Library

2001-11-27

KENNEDY SPACE CENTER, Fla. -- In the Vertical Processing Facility, members of the STS-109 crew look over the Solar Array 3 panels that will be replacing Solar Array 2 panels on the Hubble Space Telescope (HST). Trainers, at left, point to the panels while Mission Specialist Nancy Currie (second from right) and Commander Scott Altman (far right) look on. Other crew members are Pilot Duane Carey, Payload Commander John Grunsfeld and Mission Specialists James Newman, Richard Linnehan and Michael Massimino. The other goals of the mission are replacing the Power Control Unit, removing the Faint Object Camera and installing the Advanced Camera for Surveys, installing the Near Infrared Camera and Multi-Object Spectrometer (NICMOS) Cooling System, and installing New Outer Blanket Layer insulation on bays 5 through 8. Mission STS-109 is scheduled for launch Feb. 14, 2002

KSC-00pp1194

NASA Image and Video Library

2000-08-18

In the Space Station Processing Facility, Solar Array Wing-3, an element of the International Space Station, is lifted from a work stand to move it to the Integrated Electronic Assembly for testing. The solar array is scheduled to be launched on STS-97 in late November along with the P6 truss. The Station’s electrical power system (EPS) will use eight photovoltaic solar arrays to convert sunlight to electricity. Each of the eight solar arrays will be 112 feet long by 39 feet wide. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station

KSC-00pp1199

NASA Image and Video Library

2000-08-18

In the Space Station Processing Facility, Solar Array Wing-3, a component of the International Space Station, is installed in the Integrated Electronic Assembly where it will be tested. The solar array is scheduled to be launched on STS-97 in late November along with the P6 truss. The Station’s electrical power system (EPS) will use eight photovoltaic solar arrays to convert sunlight to electricity. Each of the eight solar arrays will be 112 feet long by 39 feet wide. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station

KSC-00pp1193

NASA Image and Video Library

2000-08-18

Workers in the Space Station Processing Facility get ready to move Solar Array Wing-3, a component of the International Space Station, for installation onto the Integrated Electronic Assembly. The solar array is scheduled to be launched on STS-97 in late November along with the P6 truss. The Station’s electrical power system (EPS) will use eight photovoltaic solar arrays to convert sunlight to electricity. Each of the eight solar arrays will be 112 feet long by 39 feet wide. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station

KSC-00pp1198

NASA Image and Video Library

2000-08-18

In the Space Station Processing Facility, Solar Array Wing-3, a component of the International Space Station, is installed in the Integrated Electronic Assembly where it will be tested. The solar array is scheduled to be launched on STS-97 in late November along with the P6 truss. The Station’s electrical power system (EPS) will use eight photovoltaic solar arrays to convert sunlight to electricity. Each of the eight solar arrays will be 112 feet long by 39 feet wide. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station

KSC-00pp1195

NASA Image and Video Library

2000-08-18

In the Space Station Processing Facility, Solar Array Wing-3 (at top), a component of the International Space Station, hovers above the Integrated Electronic Assembly where it will be installed for testing. The solar array is scheduled to be launched on STS-97 in late November along with the P6 truss. The Station’s electrical power system (EPS) will use eight photovoltaic solar arrays to convert sunlight to electricity. Each of the eight solar arrays will be 112 feet long by 39 feet wide. The solar arrays are mounted on a “blanket” that can be folded like an accordion for delivery. Once in orbit, astronauts will deploy the blankets to their full size. Gimbals will be used to rotate the arrays so that they will face the Sun to provide maximum power to the Space Station

KSC-05pd2409

NASA Image and Video Library

2005-11-04

KENNEDY SPACE CENTER, FLA. - At NASA Kennedy Space Center’s Payload Hazardous Servicing Facility, the New Horizons spacecraft is shrouded in insulating blankets that were installed to serve as a heat shield. Carrying seven scientific instruments, the compact 1,060-pound New Horizons probe will characterize the global geology and geomorphology of Pluto and its moon Charon, map their surface compositions and temperatures, and examine Pluto's complex atmosphere. After that, flybys of Kuiper Belt objects from even farther in the solar system may be undertaken in an extended mission. New Horizons is the first mission in NASA's New Frontiers program of medium-class planetary missions. The spacecraft, designed for NASA by the Johns Hopkins University Applied Physics Laboratory in Laurel, Md., will fly by Pluto and Charon as early as summer 2015.

Fire Protection Materials

NASA Technical Reports Server (NTRS)

1980-01-01

Avco has drawn upon its heat shield experience to develop a number of widely-accepted commercial fire protection materials. Originating from NASA's space shuttle thermal protection system, one such material is Chartek 59 fireproofing, an intumescent epoxy coating specifically designed for outdoor use by industrial facilities dealing with highly flammable products such as oil refineries and chemical plants. The coating is applied usually by spray gun to exterior structural steel conduits, pipes and valves, offshore platforms and liquefied petroleum gas tanks. Fireproofing provides two types of protection: ablation or dissipation of heat by burn-off and "intumescence" or swelling; the coating swells to about five times its original size, forming a protective blanket of char which retards transfer of heat to the metal structure preventing loss of structural strength and possible collapse which would compound the fire fighting problem.