SCAN_23-01

23-01 CHEMICAL ANALYSIS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

23-02 CHEMICAL PROCESSES AND ENGINEERING
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

23-03 LUMINESCENCE
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

23-04 PHOTOCHEMISTRY
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

24-01 REINFORCED MATERIALS AND FIBERS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

24-02 COMPOSITE MATERIALS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

25-01 CORROSION
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

25-02 METAL CRYSTALS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

25-03 COATINGS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Iodine Transport Analysis in the ESBWR
Document ID:
20090037491
Report #:
DE2009-953728, SAND2009-1702
Sales Agency:
National Technical Information Service (NTIS) No Copyright
Author(s):
Young, M. F. Longmire, P. Gauntt, R. O. Kalinch, D. A.
Published:
20090301
Source:
Sandia National Labs. (Albuquerque, NM United States)
Pages:
46
Contract #:
DE-AC04-94AL85000
Abstract:
A simplified ESBWR MELCOR model was developed to track the transport of iodine released from damaged reactor fuel in a hypothesized core damage accident. To account for the effects of iodine pool chemistry, radiolysis of air and cable insulation, and surface coatings (i.e., paint) the iodine pool model in MELCOR was activated. Modifications were made to MELCOR to add sodium pentaborate as a buffer in the iodine pool chemistry model. An issue of specific interest was whether iodine vapor removed from the drywell vapor space by the PCCS heat exchangers would be sequestered in water pools or if it would be rereleased as vapor back into the drywell. As iodine vapor is not included in the deposition models for diffusiophoresis or thermophoresis in current version of MELCOR, a parametric study was conducted to evaluate the impact of a range of iodine removal coefficients in the PCCS heat exchangers. The study found that higher removal coefficients resulted in a lower mass of iodine vapor in the drywell vapor space.
Language:
English
Notes:
Sponsored by Department of Energy, Washington, DC.

25-04 ELECTROCHEMISTRY
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Development of a Portable Oxygen Monitoring System for Operations in the International Space Station Airlock
Document ID:
20090037134
Report #:
JSC-CN-18968
Sales Agency:
Other Sources No Copyright
Author(s):
Graf, John (NASA Johnson Space Center)
Published:
20091020
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
1
Contract #:
None
Abstract:
NASA is currently engaged in an activity to facilitate effective operations on the International Space Station (ISS) after the Space Shuttle retires. Currently, the Space Shuttle delivers crew and cargo to and from ISS. The Space Shuttle provides the only large scale method of hardware return from ISS to the ground. Hardware that needs to be periodically repaired, refurbished, or recalibrated must come back from ISS on the Shuttle. One example of NASA flight hardware that is used on ISS and refurbished on the ground is the Compound Specific Analyzer for Oxygen (CSA-O2). The CSA-O2 is an electrochemical sensor that is used on orbit for about 12 months (depending on Shuttle launch schedules), then returned to the ground for sensor replacement. The shuttle is scheduled to retire in 2010, and the ISS is scheduled to operate until 2016. NASA needs a hand held sensor that measures oxygen in the ISS environment and has a 5-10 year service life. After conducting a survey of oxygen sensor systems, NASA selected a Tunable Diode Laser Absorption Spectrometer (TDLAS) as the method of measurement that best addresses the needs for ISS. These systems are compact, meet ISS accuracy requirements, and because they use spectroscopic techniques, the sensors are not consumed or altered after making a measurement. TDLAS systems have service life ratings of 5-10 years, based on the lifetime of the laser. NASA is engaged in modifying a commercially available sensor, the Vaisala OMT 355, for the ISS application. The Vaisala OMT 355 requires three significant modifications to meet ISS needs. The commercial sensor uses a wall mount power supply, and the ISS sensor needs to use a rechargeable battery as its source of power. The commercial sensor has a pressure correction setpoint: the sensor can be adjusted to operate at reduced pressure conditions, but the sensor does not self correct dynamically and automatically. The ISS sensor needs to operate in the airlock, and make accurate measurements in an environment that can change from 14.7 psia to 10.2 psia in 15 minutes. The commercial sensor needs to be repackaged into a configuration that is more compact, and better suited for ISS airlock operations. NASA has recently completed a prototype of the reconfigured system. The unit has been repackaged in a way that the optical path of the spectrometer is unchanged, but the electronics has been integrated into a case measuring 10.7 X 7.2 X 3.0 inches. Two flight qualified rechargeable batteries have been integrated into system. The batteries can power the sensor for 10 hours on a single charge. A pressure sensor has been added to the system. The modified unit automatically compensates for changes in pressure, and meets 0.2% accuracy requirements for oxygen measurements in an environment with 18 to 32% oxygen across a pressure range of 10.0 to 15.0 psia.
Language:
English
Notes:
SAMAP 2009 (Submarine Air Monitoring and Purification) San Diego, CA 20-21 Oct. 2009

26-01 ALUMINUM
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Development and Validation of Advanced Test Methods to Generate Fatigue Crack Growth and Threshold Data for Use in Damage Tolerance Analyses
Document ID:
20090037549
Report #:
PB2008-109021, DOT/FAA/AR-04/22
Available Online:
http://hdl.handle.net/2060/20090037549
Sales Agency:
CASI Hardcopy A07 No Copyright
Author(s):
Forth, S. James, M. Johnston, W.
Published:
20080201
Source:
Federal Aviation Administration (Washington, DC, United States)
Pages:
147
Contract #:
None
Abstract:
This report describes the results of a research program that determined the damage tolerance properties of metallic propeller materials. Three alloys were selected for investigation: 2025-T6 aluminum alloy, D6AC steel, and 4340 steel. Mechanical response, fatigue stress life, and fatigue crack growth rate data are presented for all the alloys. The mechanical response can be characterized using tensile tests per American Standard Test Method (ASTM) E 8. This data was used to compute yield and ultimate stresses and the elastic modulus that can be used in damage tolerance analysis tools. Fatigue testing allowed the manufacturers to verify the integrity of their in-house data and determine if material or manufacturing changes over the past years have altered the response of the material. Furthermore, this data can be used to determine an equivalent initial flaw size if the designer wishes to relate stress-life results to damage tolerance. Most importantly, the fatigue crack growth rate response of the material must be understood to predict the life of the structure from an initial detectable flaw and to set inspection intervals. This fatigue crack growth rate data was generated using ASTM E 647 and an alternative method using compression precracking. Alternative precracking methods were used to reduce load history effects when generating threshold data, producing material response data that was unaffected by the test method.
Language:
English
Notes:
Sponsored by Federal Aviation Administration, Washington, DC. Aviation Research and Development.

26-02 BERYLLIUM
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

26-03 LIQUID METALS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

26-04 STEEL
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Optimization of the SRF Cavity Design for the CEBAF 12 GEV Uugrade
Document ID:
20090037535
Report #:
DE2008-923386, JLAB-ACC-07-790, DOE/OR/23177-0311
Sales Agency:
National Technical Information Service (NTIS) No Copyright
Author(s):
Reece, C. Daly, E. Henry, J. Hicks, W. Preble, J.
Published:
20080212
Source:
Jefferson (Thomas) Lab. Computer Center (Newport News, VA, United States)
Pages:
4
Contract #:
AC05-06OR23177
Abstract:
Based on initial testing of the HG and LL 7-cell cavities in the prototype cryomodule Renascence, several opportunities for improved optimization were identified. The HOM damping configuration was refined so as to meet the requirements for damping key dipole modes while simultaneously dramatically reducing risk of HOM pickup probe heating and also creating beamline clearance for mounting the tuner to stainless steel helium vessel endplates (rather than NbTi/Ti transitions to a titanium helium vessel). Code modeling and bench measurements were performed. The new design maintains the 7-cell LL cells and incorporates a brazed transition between Nb and the SS helium vessel. The resulting configuration is now called the C100 design. Cavity design details as well as vertical dewar and horizontal test bed performance are presented.
Language:
English
Notes:
Sponsored by Department of Energy, Washington, DC.

26-05 TITANIUM
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

26-06 REFRACTORY METALS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

26-07 METALLURGY
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

27-01 PLASTICS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-02 ADHESIVES
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-03 CERAMICS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-04 ELASTOMERS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-05 GRAPHITE
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-06 POLYMERS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Towards Programmable Materials - Tunable Material Properties Through Feedback Control of Conducting Polymers
Document ID:
20090037591
Report #:
AD-A505671
Available Online:
http://hdl.handle.net/100.2/ADA505671
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Wiedenman, N. S. (Massachusetts Inst. of Tech.) Hunter, I. W. (Massachusetts Inst. of Tech.)
Journal:
Proceedings of the 26th Army Science Conference, Page: 1-8
Published:
20081201
Source:
Massachusetts Inst. of Tech. (Cambridge, MA, United States)
Pages:
9
Contract #:
None
Abstract:
This work is focused on developing an integrated device, called a programmable material, which mirrors the capabilities of natural co-fabricated controlled actuation systems such as muscle. While such a device may have the external appearance of a homogeneous material, it can possess unique properties not existing in any manufactured material. When actuation, sensing, and control capabilities are integrated within a closed-loop system, the mechanical properties of the system such as stiffness, viscosity, and inertia will arise from the dynamics of the feedback loop rather than from any inherent mechanical properties of the materials from which the device was fabricated. Moreover, these properties may be 'tuned' by altering the feedback parameters embedded in the material system. With this approach properties such as negative stiffness may be generated which do not exist in bulk materials.
Language:
English
Notes:
Presented at the Army Science Conference (26th) held in Orlando, Florida on 1-4 December 2008. Published in Proceedings of the Army Science Conference (26th), p1-8 Dec 2008. The original document contains color images 26th Army Science Conference Orlando, FL 1-4 Dec. 2008

28-01 LIQUID PROPELLANTS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Propellant Mass Fraction Calculation Methodology for Launch Vehicles
Document ID:
20090037578
Report #:
M09-0261
Sales Agency:
Other Sources Copyright
Author(s):
Holt, James B. (NASA Marshall Space Flight Center) Monk, Timothy S. (Miltec Systems Co.)
Published:
20090914
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
1
Contract #:
None
Abstract:
Propellant Mass Fraction (pmf) calculation methods vary throughout the aerospace industry. While typically used as a means of comparison between competing launch vehicle designs, the actual pmf calculation method varies slightly from one entity to another. It is the purpose of this paper to present various methods used to calculate the pmf of a generic launch vehicle. This includes fundamental methods of pmf calculation which consider only the loaded propellant and the inert mass of the vehicle, more involved methods which consider the residuals and any other unusable propellant remaining in the vehicle, and other calculations which exclude large mass quantities such as the installed engine mass. Finally, a historic comparison is made between launch vehicles on the basis of the differing calculation methodologies.
Language:
English
Notes:
American Institute of Aeronautics and Astronautics (AIAA) Space 2009 conference Pasadena, CA 14-17 Sep. 2009

28-02 SOLID PROPELLANTS
Nov 15, 2009 -- Additions to the NASA scientific and technical information knowledge base

Title:
Measurement and Characterization of Space Shuttle Solid Rocket Motor Plume Acoustics
Document ID:
20090037585
Report #:
M09-0740
Available Online:
http://hdl.handle.net/2060/20090037585
Sales Agency:
CASI Hardcopy A01 No Copyright
Author(s):
Kenny, Robert Jeremy (NASA Marshall Space Flight Center)
Published:
20090101
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
2
Contract #:
None
Abstract:
NASA's current models to predict lift-off acoustics for launch vehicles are currently being updated using several numerical and empirical inputs. One empirical input comes from free-field acoustic data measured at three Space Shuttle Reusable Solid Rocket Motor (RSRM) static firings. The measurements were collected by a joint collaboration between NASA - Marshall Space Flight Center, Wyle Labs, and ATK Launch Systems. For the first time NASA measured large-thrust solid rocket motor plume acoustics for evaluation of both noise sources and acoustic radiation properties. Over sixty acoustic free-field measurements were taken over the three static firings to support evaluation of acoustic radiation near the rocket plume, far-field acoustic radiation patterns, plume acoustic power efficiencies, and apparent noise source locations within the plume. At approximately 67 m off nozzle centerline and 70 m downstream of the nozzle exit plan, the measured overall sound pressure level of the RSRM was 155 dB. Peak overall levels in the far field were over 140 dB at 300 m and 50-deg off of the RSRM thrust centerline. The successful collaboration has yielded valuable data that are being implemented into NASA's lift-off acoustic models, which will then be used to update predictions for Ares I and Ares V liftoff acoustic environments.
Language:
English
Notes:
Year-in-Review Article