SCAN_23-01

23-01 CHEMICAL ANALYSIS
Jul 20, 2008 -- 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
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

23-03 LUMINESCENCE
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

23-04 PHOTOCHEMISTRY
Jul 20, 2008 -- 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
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

24-02 COMPOSITE MATERIALS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
A Novel Grabbing/Latching Mechanism without Moving Parts
Document ID:
20080023076
Report #:
None
Sales Agency:
CASI Hardcopy A02 Copyright
Author(s):
Gore, Brian W. (Aerospace Corp.) Hawkins, Gary F. (Aerospace Corp.)
Journal:
39th Aerospace Mechanisms Symposium, Page: 199-206
Published:
20080501
Source:
Aerospace Corp. (El Segundo, CA, United States)
Pages:
8
Contract #:
None
Abstract:
A preliminary design concept and prototype hardware have been developed for a grabbing/latching mechanism that uses no moving parts. The mechanism uses an innovative material named a Machine Augmented Composite (MAC), or MACterial, in a female configuration to accept a male bar or rod with almost imperceptible resistive force. However, when a reversing force is applied to disengage the bar/rod, it is virtually impossible to remove it due to the increasingly applied holding force. In other words, the higher the removal force applied, the higher the clamping force to resist it. The theory and physics behind this and other MACterial concepts are presented herein, as well as several potential applications that have been defined; surely there are many other applications only limited by one s imagination.
Language:
English

25-01 CORROSION
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Sulfur 'Concrete' for Lunar Applications - Environmental Considerations
Document ID:
20080022947
Report #:
NASA/TM-2008-215250, M-1223
Available Online:
http://hdl.handle.net/2060/20080022947
Sales Agency:
CASI Hardcopy A04 No Copyright
Author(s):
Grugel, R. N. (NASA Marshall Space Flight Center)
Published:
20080201
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
52
Contract #:
None
Abstract:
Commercial use of sulfur concrete on Earth is well established, particularly in corrosive, e.g., acid and salt, environments. Having found troilite (FeS) on the Moon raises the question of using extracted sulfur as a lunar construction material, an attractive alternative to conventional concrete as it does not require water. For the purpose of this Technical Memorandum, it is assumed that lunar ore is mined, refined, and the raw sulfur processed with appropriate lunar regolith to form, for example, bricks. With this stipulation, it is then noted that the viability of sulfur concrete in a lunar environment, which is characterized by lack of an atmosphere and extreme temperatures, is not well understood. The work presented here evaluates two sets of small sulfur concrete samples that have been prepared using JSC-1 lunar simulant as an aggregate addition. One set was subjected to extended periods in high vacuum to evaluate sublimation issues, and the other was cycled between room and liquid nitrogen temperatures to investigate their subsequent mechanical integrity. Results are presented from both investigations, discussed, and put into the context of the lunar environment.
Language:
English

25-02 METAL CRYSTALS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

25-03 COATINGS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Launch Lock Mechanism Design Fault Tree Use and Coatings Study
Document ID:
20080023086
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Villa, Daniel (Sandia National Labs.) Toledo, Gustavo (Sandia National Labs.)
Journal:
39th Aerospace Mechanisms Symposium, Page: 131-144
Published:
20080501
Source:
Sandia National Labs. (Albuquerque, NM, United States)
Pages:
14
Contract #:
None
Abstract:
Characteristics of a design process of a launch lock (LL) mechanism are described. This process began with generation of data that proved a previous design would not perform its function reliably. The redesign was then accomplished through the use of fault tree analysis, which helped make a better connection between requirements and actual failure scenarios. FEA modeling techniques for proper stiffness verification through testing are explored. Proto-type testing revealed that coatings at a volatile spherical joint interface became the primary area of concern as multiple configurations failed. Boron Carbide, bare AM355 to Ti6Al4V with Braycote 600EF, Tiodize, Diamond-like nano-carbon (DLN), and improperly configured coatings of MoS2 and TiCN were all shown to have unacceptable particle generation. TiCN and MoS2 doped with SbO3 and Au were shown to meet cleanliness requirements once coating parameters were properly controlled.
Language:
English

Title:
Investigation of MLF for with PZT Powder Coated Composite Laminates using ASTM Standards
Document ID:
20080023131
Report #:
None
Sales Agency:
Other Sources Copyright
Author(s):
Munjal, B. S. (Indian Space Research Organization) Sarma, P. V. B. A. S. (Indian Space Research Organization) Trivedi, H. V. (Nirma Univ. of Science and Technology)
Journal:
Journal of Spacecraft Technology, Volume 18, No. 1, Page: 48-60
Published:
20080101
Source:
Indian Space Research Organization (Ahmedabad, India)
Pages:
--
Contract #:
None
Abstract:
As per the literature survey, thin hybrid layers of viscoelastic and magnetostrictive powders can give vibration damping of smart structural systems. Though, these smart materials can be used for damping of thin flexible structural systems, they have some typical practical limitations of usage in the domain of microwave antenna applications due to sometimes EMI (Electro-Magnetic Interference) and EMC (Electro-Magnetic Coupling) issues at higher transmit and receive radio frequencies. In this paper, an attempt has been made in the hither to fore unexplored domain of investigation of the use of thin hybrid, high sensitivity ferroelectrically soft piezo electric ceramic material coatings (SP-4 and SP-5A) in lieu of Magnetostrictive powder layers for passive vibration damping effects on a wide gamut of composite materials at ambient temperature of 72.4 F(22.4 C). This paper, presents the estimation of Composite Loss Factor (CLF) or also called Modal Loss Factor (MLF) for piezo powder coated composites at ambient temperature. The encouraging results w.r.t. the MLF and increased damping at resonant frequencies for piezo coated CFRP composites, may make the investigation a possible candidate for Radio Frequency (RF) applications in future w.r.t damping out the micro-vibrations experienced in-orbit by today's sophisticated high frequency Earth observation satellite antennae reflectors with improved pointing accuracies and resolutions and that too with negligible weight penalty due to thin hybrid piezo coating.
Language:
English

25-04 ELECTROCHEMISTRY
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

26-01 ALUMINUM
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Lessons Learned Designing a Spherical Satellite Release Mechanism
Document ID:
20080023094
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Hevner, Ryan (Planetary Systems Corp.)
Journal:
39th Aerospace Mechanisms Symposium, Page: 145-156
Published:
20080501
Source:
Planetary Systems Corp. (Silver Spring, MD, United States)
Pages:
12
Contract #:
None
Abstract:
A low-cost mechanism, part of the CAPE ICU payload, was designed to contain and deploy two spherical satellites from the Shuttle in December 2006. Overall the system successfully placed the satellites into orbit but encountered an anomaly. This flight anomaly and subsequent investigation. The goal of this project was to design a release mechanism for two spherical satellites. The mechanism was to fly on a risk reduction mission to verify the design and operation of the system for a future, more ambitious mission. Because of the need to maintain a constant drag coefficient under any orientation, the satellites had no external appendages or hard points for contact. The spheres and their release systems had to be enclosed within the Canister for All Payload Ejections (CAPE). CAPE is an aluminum cylinder 0.56 m ID x 1.3 m long. The Space Test Program-H2-Atmospheric Neutral Density Experiment Risk Reduction Mission (STP-H2-ANDE RR) flew aboard Space Shuttle mission STS-116. The Naval Research Laboratory designed satellites were Mock ANDE Active (MAA) and Fence Calibration (FCal). MAA was 0.48 m in diameter and 52 kg. FCal was 0.44 m in diameter and 63 kg. MAA was desired to have a spin rate of 1-10 rpm upon orbit insertion. Each satellite was enclosed in its own cylinder. The cylinders were joined together by two Motorized Lightband separation systems (MLBs). When the MLBs separated, the satellites were simultaneously pushed out of the cylinders by compression springs. The name given to everything contained within the CAPE that separated from the Shuttle was the Internal Cargo Unit (ICU). At the end of one of the cylinders was a larger Lightband, CAPE Separation System (CSS) (see Figures 1-5). The ICU was ejected from the CAPE by means of the CSS, a 0.59-m diameter NEA-actuated Lightband separation system. Approximately 40 seconds later, two diameter 0.50-m MLBs, ICU Separation Systems (ISS), were to simultaneously separate at the center of the ICU. The lower haves of each Lightband with the motor mechanism were attached to the central Avionics Deck. The upper half of each Lightband was attached to the open end of each cylinder. Upon separation, each satellite ejected from the cylinders through the center of the upper ring.
Language:
English

26-02 BERYLLIUM
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

26-03 LIQUID METALS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

26-04 STEEL
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

26-05 TITANIUM
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Crack Detection in Armor Plates Using Ultrasonic Techniques (PREPRINT)
Document ID:
20080022930
Report #:
AD-A477861
Available Online:
http://hdl.handle.net/100.2/ADA477861
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Meitzler, Thomas J Smith, Gregory Charbeneau, Michelle Sohn, Euijung Bienkowski, Mary Wong, Ivan Meitzler, Allen H
Published:
20070301
Source:
Army Research Development and Engineering Command (Warren, MI United States)
Pages:
7
Contract #:
None
Abstract:
A method of using piezoelectric lead zirconate titanate (PZT) transducers to characterize the vibrational modes of Vehicle Body Armor Support System (VBASS) plates and its preliminary results are presented. The amplitude of the vibrational modes of undamaged plates are compared to the vibrational mode amplitudes of damaged plates and shown to be clearly different. Plates for testing are damaged either by a blunt impact to the ceramic plate surface or cracked using a machine shop press. Data from these tests will be used to design prototype hand-held devices for the nondestructive testing (NDT) of plate structural in the field. VBASS plates are used as proof-of-principle saniples in the absence of vest body arnior saniples.
Language:
English
Notes:
Submitted for publication in "The American Society for Nondestructive Testing" - Materials Evaluation

Title:
Sonic Fatigue Testing of a Functionally Graded Ti/TiB Material
Document ID:
20080022931
Report #:
AD-A477877, AFRL-RB-WP-TR-2008-3021
Available Online:
http://hdl.handle.net/100.2/ADA477877
Sales Agency:
Defense Technical Information Center (DTIC) No Copyright
Author(s):
Byrd, Larry Tuegel, Eric J Quast, Jeffrey Boehlert, Carl
Published:
20080101
Source:
Air Force Research Lab. (Wright-Patterson AFB, OH United States)
Pages:
147
Contract #:
None
Abstract:
The objective of this program was to determine how a functionally graded metal-ceramic material responds to high-frequency loading that is characteristic of sonic fatigue. This material has potential use as skins of aerodynamically heated structure and will experience fluctuating pressure that may result in sonic fatigue. Fatigue cracking starts in the brittle ceramic-rich layer. It was thought that the ductile metal-rich layers would increase the life of the specimen over a monolithic ceramic-rich specimen. This could not be confirmed nor refuted with the limited test data obtained. It was clear that a better sonic fatigue test method is needed for these types of materials. The current test method does not maintain sufficient control of the test.
Language:
English

Title:
Cryogenic Focus Mechanism for the Spitzer Space Telescope
Document ID:
20080023067
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Schade, William C. (Ball Aerospace and Technologies Corp.)
Journal:
39th Aerospace Mechanisms Symposium, Page: 401-414
Published:
20080501
Source:
Ball Aerospace and Technologies Corp. (Boulder, CO, United States)
Pages:
14
Contract #:
None
Abstract:
A new focus mechanism was developed, tested, and flown for the Spitzer Space Telescope ("Spitzer"), one of NASA s "Great Observatories". Figure 1 shows the Flight Focus Mechanism (FLT-FM), now in Spitzer. The mechanism uniquely provides robust support and precise focus adjustment for the Spitzer secondary mirror, from 300 K to a 5 K cryogenic environment. This paper summaries the requirements, performance, description, and testing of the focus mechanism, including key component level tests of a geared-stepper motor and ball screw. Also, a secondary mirror mount is described that minimizes mirror distortion and supports high loads. Several design and test challenges were overcome and lessons learned from this successful development include: a) Titanium is useful as a flexure material to liquid helium temperatures. b) Adhesive bonds at cryo-temperatures should be well understood and / or tested. c) Geared-stepper motor and ball screw components were simply modified to work to < 5 K.
Language:
English

26-06 REFRACTORY METALS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Physical and Mechanical Properties of Niobium for SRF Science and Technology
Document ID:
20080022292
Report #:
DE2007-909317
Sales Agency:
National Technical Information Service (NTIS) No Copyright
Author(s):
Myneni, G. R.
Published:
20070101
Source:
Thomas Jefferson National Accelerator Facility (Newport News, VA, United States)
Pages:
7
Contract #:
None
Abstract:
Optimized mechanical and physical properties of high purity niobium are crucial for obtaining high performance SRF particle beam accelerator structures consistently. This paper summarizes these important material properties for both high purity polycrystalline and single crystal niobium.
Language:
English

26-07 METALLURGY
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-01 PLASTICS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-02 ADHESIVES
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-03 CERAMICS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Performance of the First Refurbished CEBAF Cryomodule
Document ID:
20080022290
Report #:
DE2007-909320
Sales Agency:
National Technical Information Service (NTIS) No Copyright
Author(s):
Drury, M. Daly, E. F. Davis, G. K. Fischer, J. Grenoble, C.
Published:
20070101
Source:
Jefferson (Thomas) Lab. Computer Center (Newport News, VA, United States)
Pages:
3
Contract #:
DE-AC05-06OR23177
Abstract:
The Thomas Jefferson National Accelerator Facility has begun a cryomodule refurbishment project. The goal of this project is robust 6 GeV, 5 pass operation of the Continuous Electron Beam Accelerator Facility (CEBAF). The scope of the project includes removing, refurbishing and replacing 10 CEBAF cryomodules at a rate of three per year. Refurbishment includes reprocessing of SRF cavities to eliminate field emission and increase the nominal gradient from the original 5 MV/m to 12.5 MV/m. New dogleg couplers between the cavity and helium vessel flanges will intercept secondary electrons that produce arcing on the 2 K ceramic window in the Fundamental Power Coupler (FPC). Modification of the Qext of the FPC will allow higher gradient operations. Other changes include new ceramic RF windows for the air to vacuum interface of the FPC and improvements to the mechanical tuners. Any damaged or worn components will be replaced as well. Currently, the first of the refurbished cryomodules has been installed and tested both in the Cryomodule Test Facility and in place in the North Linac of CEBAF. This paper will summarize the results of these tests.
Language:
English

Title:
Picosecond Bunch Length and Energy-z Correlation Measurements at SLAC's A-Line and End Station A
Document ID:
20080022296
Report #:
DE2007-909304, SLAC-PUB-12598
Sales Agency:
National Technical Information Service (NTIS) No Copyright
Author(s):
Molloy, S. Emma, P. Frisch, J. Iverson, R. Ross, M.
Published:
20070601
Source:
Stanford Linear Accelerator Center (Menlo Park, CA, United States) Lawrence Livermore National Lab. (Livermore, CA United States)
Pages:
3
Contract #:
DE-AC02-76SF00515
Abstract:
We report on measurements of picosecond bunch lengths and the energy-z correlation of the bunch with a high energy electron test beam to the A-line and End Station A (ESA) facilities at SLAC. The bunch length and the energyz correlation of the bunch are measured at the end of the linac using a synchrotron light monitor diagnostic at a high dispersion point in the A-line and a transverse RF deflecting cavity at the end of the linac. Measurements of the bunch length in ESA were made using high frequency diodes (up to 100 GHz) and pyroelectric detectors at a ceramic gap in the beamline. Modelling of the beams longitudinal phase space through the linac and A-line to ESA is done using the 2-dimensional tracking program LiTrack, and LiTrack simulation results are compared with data. High frequency diode and pyroelectric detectors are planned to be used as part of a bunch length feedback system for the LCLS FEL at SLAC. The LCLS also plans precise bunch length and energy-z correlation measurements using transverse RF deflecting cavities.
Language:
English

Title:
Novel Noncontact Method for Simultaneously Measuring Absolute Thickness and Physical Density in Dielectric Materials
Document ID:
20080023143
Report #:
None
Sales Agency:
Other Sources Copyright
Author(s):
Roth, Donald J. (NASA Glenn Research Center) Seebo, Jeffrey P. (Lockheed Martin Space Operations) Winfree, W. P. (NASA Langley Research Center)
Published:
20070101
Source:
NASA Glenn Research Center (Cleveland, OH, United States)
Pages:
27
Contract #:
None
Abstract:
This article describes a noncontact single-sided terahertz electromagnetic measurement and imaging method that simultaneously measures density and thickness variation in dielectric (insulating) materials. The method was demonstrated for two materials--Space Shuttle External Tank sprayed-on foam insulation and a silicon nitride ceramic. It is believed that this method can be used as a noncontact measurement method for dielectric materials backed by a conducting or semi-conducting material where density and thickness variation require precision mapping for the dielectric.
Language:
English
Notes:
Submitted to Measurement Science and Technology Institute of Physics

27-04 ELASTOMERS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

27-05 GRAPHITE
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

27-06 POLYMERS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Evaluation of Perfluoropolyether Lubricant Lifetime in the High Stress and High Stress-Cycle Regime for Mars Applications
Document ID:
20080023091
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Herman, Jason (Honeybee Robotics Ltd.) Davis, Kiel (Honeybee Robotics Ltd.)
Journal:
39th Aerospace Mechanisms Symposium, Page: 69-82
Published:
20080501
Source:
Honeybee Robotics Ltd. (New York, NY, United States)
Pages:
14
Contract #:
None
Abstract:
The successful operation of long-life, highly loaded mechanisms used for planetary exploration or autonomous structures assembly will depend upon the ability to effectively lubricate rolling-element bearings. As new tools are developed (i.e., drill, abraders, robotic manipulators, etc.) that interact with their environment in a more direct manner, lubricants will be pushed past the bounds that current scientific literature has published. This paper details results from bearing lubrication lifetime testing performed in support of Honeybee Robotics development of the Mars Science Laboratory (MSL) Surface Removal Tool (SRT). This testing was done due to the lack of available data in research literature that is applicable to the lubrication regime the SRT bearings are being designed for. Based on the test results, the chosen bearing arrangement can be used for the SRT Grind Shaft bearings with the use of a Braycote Micronic 601EF grease-plate with a 10 vol% grease slurry fill (50/50 wt% Braycote Micronic 601EF and Brayco 815Z). This arrangement showed no signs of detrimental degradation over the course of the 3x life test. The purely grease-plated bearing ran at a consistently higher torque and showed signs of failure beginning at approximately 2.2 x 10(exp 7) revs (approximately 6.3 x 10(exp 7) stress-cycles) with a torque over-limit failure at approximately 4.5 x 10(exp 7) revs (approximately 1.3 x 10(exp 8) stress-cycles). Barring cold-start torque margin limitations, it is recommended that any long-life bearing application include some vol% grease-pack in addition to a standard grease-plate to reduce parasitic torque and increase bearing life. While these results are specific to a particular environment and loading condition, they demonstrate the extended capabilities of a commonly used flight lubricant outside of the range that is published in current research literature.
Language:
English

28-01 LIQUID PROPELLANTS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

28-02 SOLID PROPELLANTS
Jul 20, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Gas Strut Separation Alternative for Ares I
Document ID:
20080023072
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Floyd, Brian (NASA Marshall Space Flight Center) Owens, James (NASA Marshall Space Flight Center)
Journal:
39th Aerospace Mechanisms Symposium, Page: 331-344
Published:
20080501
Source:
NASA Marshall Space Flight Center (Huntsville, AL, United States)
Pages:
14
Contract #:
None
Abstract:
This paper presents a design alternative and the rationale for a stage separation system based on Metering Adiabatic Gas Struts (MAG Struts) for the Ares 1 launch vehicle. The MAG Strut separation system was proposed as an alternative to the current Ares 1 separation system, which relies on small solid rocket motors to provide the main separation force. This paper will describe technical issues that were addressed during the trade study and present a conceptual design of the strut system that best resolved the issues. Needed development testing and programmatic considerations will be addressed as part of the paper.
Language:
English