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Non-metallic materials A Fire-Resistant Epoxy : Final Report This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-01/53, by Richard E. Lyon, Lauren M. Castelli, and Richard Walters, dated August 2001. This study examines the fire, flammability, thermal, and mechanical properties of DGEBC and DGEBA epoxies polymerized by four different mechanisms. The full text of the report is available in PDF format from the online catalogue of the FAA William J. Hughes Technical Center Library. Advanced Manufacturing Research Centre (AMRC) The Advanced Manufacturing Research Centre (AMRC) is a partnership between the University of Sheffield and Boeing. Its aim is to become a world-class global research facility developing innovative and advanced technology solutions for advanced materials forming. The site provides detailed information about AMRC's core research areas (structural integrity, dynamic analysis, damping, surface integrity, virtual reality, machining, complexity, manufacturing management, additive processes and thixo-forming), and a list of publications. Activities within schools and FE colleagues are described as are services that can be offered to industry (e.g. consultancy, rapid prototyping). There is also an FAQ, a news archive, and a career opportunities section. Part of the site is for members only, AEA Technology AEA Technology focuses on five key areas: technology-based products, specialised science, environmental management, improving the efficiency of industrial plant, and risk assessment and safety management. The site describes the capabilities, products and services of the company. There is a site search facility and a products and services catalogue which can be searched and browsed. The 'investor relations' area provides annual reports and account information from 1997 in PDF format. Up-to-date company news is available. Aeropia Aeropia supplies chemicals and associated materials to the aerospace and engineering industries. This company site provides access to lists of products and services. It contains contact details, direct e-mail and enquiry facilities. AGARD engine disc cooperative test programme This is Research and Technology Organization (RTO) AGARD-R-766 , dated August 1988. The initial results of an AGARD test program on fatigue behavior of engine disc materials are described. The first phase of the program, the Core Program, was aimed at test procedure and specimen standardization and calibration of the various laboratories. A detailed working document is included which describes the testing fundamentals and procedures and includes the analysis procedures used for handling the test data. Fatigue crack initiation and propagation testing was performed on Ti-6Al-4V material under room temperature and constant amplitude loading conditions using four different specimen designs. All results were statistically analyzed for possible significant differences in material behavior due to disc processing variables, specimen location in the disc or testing laboratory. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (121.10MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Aircraft Materials Fire Test Handbook This web site provides access to a Federal Aviation Administration Report titled: Aircraft Materials Fire Test Handbook, compiled by April Horner, DOT/FAA/AR-00/12, April 2000. The handbook describes all FAA-required fire test methods for aircraft materials. The appendices contain the following: FAA fire safety regulations; FAA approval processes; aircraft materials; regulatory methodology used by other countries; aircraft industry internal test methods and guidelines; laboratories actively using fire test methods, and commercial manufacturers of fire test equipment. The full text of the handbook is available online in PDF format. Aircraft Wiring Degradation Study This technical report (DOT/FAA/AR-08/2) was published by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in January 2008 and was written by Robert Bernstein, Mike Etheridge, Gary LaSalle, Roy McMahon, Jim Meiner, Noel Turner, Michael Walz and Cesar Gomez. The purpose of this initial research program was to evaluate the aging characteristics of three types of aircraft electrical wire: polyimide, poly trafluoroethylene/polyimide composite, and polyvinyl chloride/nylon. In addition, predictive models forthe aging of these wire types were developed. These wire types were chosen because of their widespread use in commercial aircraft and the amount of reported incidents concerning them. The factors that cause the wire insulation to degrade were examined and techniques to determine when a wire will no longer be capable of transfer of electrical current were evaluated. The results in this study provided a platform to evaluate existing and new test methods that could be used to monitor the aging of wire in aircraft. The results found were similar to the aging samples found from the Aging Transport Systems Rulemaking Advisory Committee Intrusive Inspection Report. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Applied Aerospace Structures Corporation This is the web site of the Applied Aerospace Structures Corporation (AASC), a US company involved in the manufacture of lightweight composites and metallic structures and components for space and aircraft applications. The focus of the company is on creating high strength lightweight structures for aircraft and spacecraft. The site gives some background information about the company and also gives details about its products and services. These are divided into five main product areas - space, aircraft, precision structures, ground systems, engineering and testing. It is possible to view the full text of the company's press releases. ASME Digital Library This service allows you to search ASME (American Society of Mechanical Engineers) journal articles back to 1985 and conference proceedings back to 2002. Search results provide bibliographic information and an abstract, with the option to purchase the full text, if you are not a subscriber. Aviation Oil Lead Content Analysis This provides access to a Federal Aviation Administration (FAA) report EPA-2007-0294 prepared by Todd Petersen dated January 2008. In November and December 2007, samples of used aviation oil were collected at three Nebraska airports. The samples were taken from airplanes using 100LL exclusively. Ten samples were obtained and subsequently analyzed for lead at the end of December. Sample eleven consisted of new, unused Aeroshell 100W. Aviation Labs in Kenner, LA did the analysis. Results of the analysis may be reached on the Internet by going to: http://avlab.com/analysis/login/default.asp The Customer Code is “ptrav”. Insert “ptrava” for engine serial number. [Taken from abstract]. The full text is available on PDF format so Adobe Acrobat software is required in order to read it. Axisymmetric Optical Membrane Modeling Based on Experimental Results This is the full text of a thesis by Brian J. Lutz which was presented to the Air Force Institute of Technology (AFIT) in 2004. The United States Air Force, Department of Defense and commercial industry have recognized the great value of near-earth space development, specifically in satellites for use in communications, ground and space surveillance and more active roles. However, resolution, or the primary optics diameter, has been a limitation, especially for ground surveillance. Deployable optics has been investigated to allow larger optics in space and membrane optics has received increasing attention recently. The membranes flexible nature requires some passive and possibly active control to reduce optical distortion caused by manufacturing, deployment, or other effects during use. Piezoelectric surface controllers are one option to actively control the membrane on the order of optical measurements (micron displacement or less). Multiple configurations of transverse displacements are feasible depending on the piezo zone locations and activation. The current thrust of industry is reducing the effort, time and cost of manufacturing and testing through use of computerized modeling and simulation; therefore, this was investigated for a membrane mirror and piezoelectric combination. Prior experiments using 6-inch diameter membranes have been conducted with an axisymmetric piezoelectric material layer on the non-optical surface. Various voltage differentials were applied to the piezo and the transverse displacement was measured. A finite element code, using perturbation techniques, was written in MATLAB and tested to check the feasibility of using computer models for the micro-displacements occurring with the membrane-piezo lay-up. The computer program considered was developed for axisymmetric conditions; however, in many cases, these conditions tended to dominate. Under these conditions, the finite element code produces results that represent the axisymmetrically reduced experimental data. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site. Battle Damage Modeling
This is the full text publication that was assembled to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel (AVT) presented on 17-18 May 2010 in Prague, Czech Republic. Bioremediation of Aircraft Deicing Fluids (Glycol) at Airports This final report (DOT/FAA/AR-97/81) was published by the Federal Aviation Administration (FAA) in August 1998, and was written by Donald W. Gallagher. It describes the work done to determine the effectiveness of various aerobic bioremediation techniques for reducing the biochemical oxygen demand (BOD) of aircraft deicing fluid runoff. Primary emphasis has been placed on laboratory and field demonstrations of bioremediation systems using various combinations of inocula (bacteria), nutrient mixes, enzyme mixes, and ultrasonic stimulation [extracted from FAA abstract]. This is a PDF file [21 pages, 139Kb] so Adobe Acrobat software will be required in order to read it. Burner Rig Testing of "Herringbone" EB-PVD Thermal Barrier Coatings This technical report (NLR-TP-2002-293) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 2002 and was written by M.F.J. Koolloos and G. Marijnissen. In order to lower the thermal conductivity of Electron Beam-Physical Vapour Deposited Thermal Barrier Coatings (EB-PVD TBCs), so-called "herringbone" TBCs with a zig-zag or wavy column structure have been developed. This structure can result in more than 25 % reduction in thermal conductivity compared to a straight column TBC. This paper focuses on burner rig tests which were done to assess the service life of herringbone TBCs. Burner rig tests at 1135 ?d with a cycle length of 5 minutes showed that the number of cycles to failure of the herringbone TBCs was comparable to but lower than that of reference straight column TBCs. Furthermore, the symmetric zig-zag TBCs showed erosion at the flame-heated side. It is concluded that though the new herringbone TBCs show promising thermal properties, the production process must be optimised to improve the life and flame erosion resistance. [Taken from abstract]. The full text is available as a PDF file. Characterization of Functionally Graded Materials This is the full text of a Master's thesis by Second Lieutenant Benjamin D. Chapman, USAF, AFIT/GAE/ENY/06-M05, which was presented to the Faculty Department of Aeronautics and Astronautics of Air University's Air Force Institute of Technology (AFIT), in March 2006. The purpose of this study was to characterize the behavior of a functionally graded material through experimentation and analytical modeling. Functionally graded materials are a ceramic metal composite which transitions from metal on one face to ceramic on the opposite face. Creating reliable models required verifying the material properties. This was accomplished through the use of a static modulus of elasticity test as well as a dynamic ping test. The natural frequencies from the dynamic test were compared with finite element models to determine which material properties most accurately represented the functionally graded material. It was found that the material properties established experimentally by Hill and Lin produced the best models. A fracture surface was examined to determine the failure criteria for the prediction of failure in a cyclic loading scenario. It was determined that the material would fail in a brittle manner and the maximum principle stresses should be used to predict failure. Finally, a model was generated to analyze the through-the-thickness stresses in the material under a sinusoidal forcing function. It was determined that the majority ceramic upper layer was the critical layer for failure and required an amplitude of 5.83 KN to reach failure in the specimen. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC). Characterization of Residual Stress in Microelectromechanical Systems (MEMS) Devices using Raman Spectroscopy This is the full text of a thesis by Lavern A. Starman which was presented to the Air Force Institute of Technology (AFIT) in 2002. Due to the unique structure and small scale of Micro-Electro-Mechanical Systems (MEMS), the inherent residual stresses during the deposition processes can have a profound affect on the functionality and reliability of the fabricated MEMS devices. Residual stress often causes device failure due to curling, buckling, or fracture. Typically, the material properties of thin films used in surface micromachining are not controlled during deposition. The residual stress, for example, tends to vary significantly for different deposition methods. Currently, few techniques are available to measure the residual stress in MEMS devices. In this dissertation research, I use mRaman spectroscopy to measure the residual and induced stresses in MUMPs polysilicon and GaAs MEMS devices. mRaman spectroscopy was selected since it is nondestructive, fast, and provides the potential for in situ stress monitoring. I performed Raman spectroscopy line and mapping scans to obtain Raman residual stress profiles on unreleased and released MEMS fixed-fixed beams, cantilevers, and micromirror fexures. These profiles were compared to analytical models to assess the accuracy of the Raman stress profiles. Finite element residual and induced stress profiles are obtained from MEMCAD modeling software and used to assess the viability of mRaman spectroscopy as an in situ stress measurement technique. I performed several post-processing techniques to include thermal annealing, phosphorous diffusion, and phosphorous ion implantation to investigate methods to alter or control the residual stress within MEMS devices. mRaman spectroscopy is used to characterize and monitor the residual stress levels in the unreleased MEMS structures following each post-processing experiment to determine the magnitude of stress relaxation. Significant residual stress relaxation is observed in the Raman stress profiles and verified with on-chip test structures following the thermal anneals and doping. The MUMPs foundry fabricated residual stress levels can be significantly reduced by over 90% to stress levels less than 1 MPa following post-processing. The reduced residual stress levels can significantly improve device performance, reliability, and yield as MEMS devices become smaller. In addition to the polysilicon stress profiles, the first mRaman stress measurements in III-V MEMS is presented. [Taken from abstract]. The full text of the thesis is available in PDF format and isprovided by the Air University ResearchWeb site. Characterization of the Optical and Electrical Properties of Proton-Irradiated 4H-Silicon Carbide This is the full text of a thesis by Heather C. Crockett which was presented to the Air Force Institute of Technologyt (AFIT) in 2002. Epitaxial n-type 4H-silicon carbide (SiC) is irradiated with 2 MeV protons to evaluate the dislocation damage effects on the optical and electrical characteristics of the material. Semiconductor materials with a high tolerance to radiation fields have applications in several aerospace power and satellite systems. SiC is under investigation due to its potential for such space material applications. The effects of proton irradiation on the optical properties of the material are investigated using temperature-dependant photoluminescence (PL) and the effects of proton irradiation on the electrical properties are evaluated using current-voltage measurements and constant-voltage deep level transient spectroscopy (CV-DLTS). Subsequent high-temperature thermal annealing and recovery of the irradiated material is investigated over the temperature range of 900 1500 C. Proton-induced irradiation damage is apparent in the 4H-SiC material, affecting both the optical and electrical characteristics of the devices. The radiative behavior of the nitrogen-related near band edge transitions is significantly reduced as a result of the irradiation, with partial recovery observed after high-temperature thermal annealing at 1500 C. A deeper trapping complex (EC ET .380 meV) is detected as a result of irradiation and shows signs of activation due to thermal annealing. Previous research investigating ion-implantation in 4H-SiC suggests that these traps are generated independent from the type of particle implantation. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site. Combustibility of Cyanate Ester Resins This technical report (DOT/FAA/AR-02/44) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in June 2002 and was written by Richard E. Lyon, Richard Walters and S. Gandhi. Flaming and nonflaming combustion studies were conducted on a series of polycyanurates to examine the effect of chemical composition and physical properties on the fire behavior of these cross-linked, char-forming thermoset polymers. Heats of complete combustion of the polymer and fuel gases were determined by oxygen bomb calorimetry and pyrolysis-combustion flow calorimetry, respectively. Fire calorimetry experiments were conducted to measure the heat released, the rate of heat release, and the smoke generation in flaming combustion. Fire response parameters derived from the data include the thermal inertia, heat of gasification, effective heat of combustion, and combustion efficiency. Halogen-containing polycyanurates exhibited extremely low heat release rate in flaming combustion compared to the hydrocarbon resins, yet produced significantly less smoke and comparable levels of carbon monoxide and soot. [Taken from abstract] This is a PDF file, so Adobe Acrobat software will be required in order to read it. Computational Science and Engineering Department (STFC) The Computational Science and Engineering (CSE) activities within the UK's Science and Technology Facilities Council provide world-class expertise and support for the UK theoretical and computational science communities, in both academia and industry. The cost-effective and efficient services are enabling predictions from complex theories to be calculated from first principles and be compared directly with experimental data. The computational activity within CCLRC has grown significantly in recent years. The major output of the CSE Department is the development and application of powerful simulation codes, usually in collaboration with university research groups. They place particular emphasis on achieving very high performance; advancing the basic computational methods to tackle new scientific challenges on new generations of hardware. There is an undergoing development of high-performance applications in core areas of quantum chemistry, molecular simulation, solid-state physics, materials simulation, engineering and environmental simulations. The group has collaborations with theoreticians and computational scientists in the universities and colleagues within the experimental facilities at CCLRC. In addition to the core applications, there is also support to a number of data activities such as the Chemical Database Service. The website provides useful information and links regarding publications, semimar programs, collaborative projects, research networks, high performace computing within the Uk. Additionally, the website provides information for advace research on subjects such as, atomic and molecular physics, band theory, CCP4 group, computational chemistry, computational engineering, computational material science, numerical analysis, software engineering. Cooperative creep testing programme This is Research and Technology Organization (RTO) AGARD-R-581, dated March 1971. Creep testing at elevated temperatures is an expensive and time-consuming business. Nevertheless, creep tests are frequently duplicated, there appears to be little confidence in creep data obtained from other laboratories. The AGARD Working Group on High-Temperature Material Testing was established in 1966 with the aim of improving the specifications and raising the standard of determination of the mechanical properties of materials at high temperatures in the NATO countries. This report describes the results accomplished. The results of creep and creep rupture measurements are subject to seemingly wide scatter. The major contributing factors have generally been qualitatively related to inhomogeneity of commercial materials and to inherent or inadequately controlled testing techniques and instrumentation. The latter sources of variability may be lessened by improved design of equipment and by improved specifications. The problem is of primary importance to metallurgists involved in the development of new materials, and also, to design engineers. Time and again creep laboratories are getting involved in interlaboratory evaluations of data either on the basis of private initiatives or within the framework of national or international cooperative programmes. During the preliminary discussions of the Working Group on High Temperature Testing of the Structures and Materials Panel of AGARD, it appeared that the implementation of a programme involving testing conditions currently encountered in superalloy technology, would be desirable. In summary, the objectives of the programme may be outlined as follows: (a) the comparison of creep and stress rupture data from different laboratories (b) the determination or estimation of relevant standard deviations (c) the evaluation of the adequacy of current specifications and testing techniques (d) the identification of possible significant sources of variability for further investigation (e) the establishment of a standard lot of material for use within laboratories in NATO countries (f) the determination for the material used of statistically significant creep data. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (11.85MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Delphion Patent Search Form This site allows you to search for United States patents, European patents and patent applications, Patent Cooperation Treaty (PCT) application data from the World Intellectual Property Office, the Patent Abstracts of Japan and INPADOC data. The service can be searched in several different ways, including patent number, US classification and Boolean keyword search. It is possible to view to the bibliographic information of granted US patents free of charge, all other services are payable. You will need to register to use this service, which is free of charge. Design of Repair for Battle Damaged Rotary Wing Aircraft
This is the full text publication that was assembled to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel (AVT) presented on 17-18 May 2010 in Prague, Czech Republic. Design of Repair of Battle-Damaged Fixed-Wing Aircraft
This is the full text publication that was assembled to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel (AVT) presented on 17-18 May 2010 in Prague, Czech Republic. Detection of Residual Stress in SiC MEMS Using micro-Raman Spectroscopy This is the full text of a Master's thesis by First Lieutenant John C. Zingarelli, USAF, AFIT/GEO/ENP/05-06, which was presented to the Faculty Department of Engineering Physics of Air University's Air Force Institute of Technology (AFIT), in March 2005. Micro-Raman (mu-Raman) spectroscopy is used to measure residual stress in two silicon carbide (SiC) poly-types: single-crystal, hexagonally symmetric 6H-SiC, and polycrystalline, cubic 3C-SiC thin films deposited on Si substrates. Both are used in micro-electrical-mechanical systems (MEMS) devices. By employing an incorporated piezoelectric stage with submicron positioning capabilities along with the Raman spectral acquisition, spatial scans are performed to reveal areas in the 6H-SiC MEMS structures that contain residual stress. Shifts in the transverse optical (TO) Stokes peaks of up to 2 cm^-1 are correlated to the material strain induced by the MEMS fabrication process through the development of phonon deformation potential curves for this material. The 3C-SiC films, with thicknesses ranging from 1.5-5 microns, are deposited by CVD on (100) Si substrates and are also investigated to determine their residual stress. An ultraviolet excitation source (lambda = 325 nm, hv = 3.82 eV) was determined to be more effective for the detection of Raman shifts in these thin films than the 514-nm source, since the absorption coefficient in SiC at 300 K at 325 nm is 3660 cm-1, while that at 514 nm is less than 100 cm-1. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC). Determination of Fuel/Air Mass Ratios for Jet Fuels at their Flash Point Temperatures This technical report (DOT/FAA/AR-02/96) was published by the Federal Aviation Administration (FAA) Office of Aviation Research in September 2006 and was written by James E. Woodrow. The goal of this project was to determine fuel vapor densities and, ultimately, fuel-to-air mass ratios (FAMRs) for 11 commercial jet fuels at their flash point temperatures. The vapor composition of each fuel sample was modeled at each flash point temperature, rounded to the nearest whole value, using an alkane reference standard (pentane), with the results expressed as total vapor density for each fuel sample. In addition, the liquid composition of each fuel sample was modeled using 16 alkane reference standards (C5-C20), again with the results expressed as total vapor density. From these vapor density values, FAMRs were derived. From the determination of vapor composition, the measured vapor densities fell in the range 44.0-54.0 g/m3, depending on the flash point temperature, and the FAMRs fell in the range 0.041-0.047, with an average value of 0.044 and a percent relative standard deviation (%RSD) of 4.5. Based on the liquid composition, vapor densities calculated for the exact flash point temperatures fell in the range 46.5-50.4 g/m3, and the FAMRs fell in the range 0.043-0.045, with an average value of 0.044 and a %RSD of 2.3. These results demonstrate that the FAMR is a constant value at the flash point and this value is 0.044. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Determination of the Heats of Gasification of Polymers Using Differential Scanning Calorimetry This technical report (DOT/FAA/AR-TN07/62) was published by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in November 2007 and was written by Stanislav I. Stoliarov and Richard N. Walters. The amount of heat that is required to gasify unit mass of material is one of the key properties that define its ignition resistance and fire response. Knowledge of this property is necessary to assess a material’s fire hazard in a particular fire scenario. Nevertheless, even for the most common polymers, the values of this property are not well established. Here, a methodology is presented for determining the heat of gasification using differential scanning calorimetry and applying this methodology to a set of ten common plastics and engineering polymers. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Determination of the Heats of Gasification of Polymers Using Differential Scanning Calorimetry This technical report (DOT/FAA/AR-TN07/62) was published by the Fire Safety Branch of the Federal Aviation Administration (FAA) in November 2007 and was written by Stanislav I. Stoliarov and Richard N. Walters. The amount of heat that is required to gasify unit mass of material is one of the key properties that define its ignition resistance and fire response. Knowledge of this property is necessary to assess a material’s fire hazard in a particular fire scenario. Nevertheless, even for the most common polymers, the values of this property are not well established. Here, a methodology is presented for determining the heat of gasification using differential scanning calorimetry and applied to a set of ten common plastics and engineering polymers. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Determining the Resistivity of Resistive Sheets Using Transmission Measurements This is the full text of a Master's thesis by Captain Milo W. Hyde, USAF, AFIT/GE/ENG/06-24, which was presented to the Faculty Department of Electrical and Computer Engineering of Air University's Air Force Institute of Technology (AFIT), in March 2006. In September 2005, radar cross section (RCS) measurements were made of resistive sheets, or R-cards, wrapped around a polystyrene foam cylinder to compare with a newly developed theoretical RCS prediction technique. The resistivities of the R-cards were initially measured with a direct current (DC) four-point probe. When the RCS measurements were compared to the theoretical predictions, it became clear that DC resistivity alone is not sufficient to accurately predict the scattering from an R-card. This thesis presents alternating current (AC) methods for determining the resistivity of an R-card. Both freespace and waveguide techniques are presented. Experimental verification of the techniques is performed using two R-cards with DC resistivities 892 Ω/sq and 64 Ω/sq. The techniques are compared intraand inter-measurement apparatus. An error analysis is also performed to demonstrate the sensitivity of the techniques to errors in the measurements of the thickness or the permittivity of the support backing. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC). Development and Performance of an Adiabatic Expansion Nozzle for Improved Fire Extinguishers This technical report (DOT/FAA/AR-TN01/60) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in December 2001 and was written by Robert Z. Filipczak. A new fire extinguisher concept, the adiabatic expansion nozzle, extends the usefulness of fire extinguishing compounds by lowering the temperature and discharge pressure of the agent. This allows total flood type halon replacements to be used in hand- held applications and, in the instance of carbon dioxide, produces a low-pressure dry ice snow. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Development and Testing of Flame Retardant Additives and Polymers This technical report (DOT/FAA/AR-07/25) was produced by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in April 2007 and was written by Joshua L. Jurs. Novel flame-retardant chemical additives and polymers were synthesized and their flammability measured in the Underwriters Laboratory test for flammability of plastics (UL94). Self-extinguishing (V-0) compositions were obtained for poly (acrylonitrile-butadiene-styrene) and high-impact polystyrene by adding as little as 10 weight percent of boronic acid derivatives or halogen-containing bisphenylethenes (BPH). Self-extinguishing (V-2) compositions were obtained for polyethylene by adding as little as 10 weight percent BPH. The efficacy of BPH additives as flame-retardants suggested incorporating these moieties directly into the polymer to further reduce flammability. Polymers and copolymers were synthesized having BPH backbone and pendant groups, including backbone copolymers containing acetylene and phosphineoxide. The thermal combustion properties of polymers containing a BPH backbone or pendant groups were measured by microscale combustion calorimetry and found to be among the lowest values ever recorded, suggesting that aircraft cabin materials made from these polymers would be ultra-fire-resistant. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Development and Testing of Flame Retardant Additives and Polymers This technical report (DOT/FAA/AR-07/25) was produced by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in April 2007 and was written by Joshua L. Jurs. Novel flame-retardant chemical additives and polymers were synthesized and their flammability measured in the Underwriters Laboratory test for flammability of plastics (UL94). Self-extinguishing (V-0) compositions were obtained for poly (acrylonitrile-butadiene-styrene) and high-impact polystyrene by adding as little as 10 weight percent of boronic acid derivatives or halogen-containing bisphenylethenes (BPH). Self-extinguishing (V-2) compositions were obtained for polyethylene by adding as little as 10 weight percent BPH. The efficacy of BPH additives as flame-retardants suggested incorporating these moieties directly into the polymer to further reduce flammability. Polymers and copolymers were synthesized having BPH backbone and pendant groups, including backbone copolymers containing acetylene and phosphineoxide. The thermal combustion properties of polymers containing a BPH backbone or pendant groups were measured by microscale combustion calorimetry and found to be among the lowest values ever recorded, suggesting that aircraft cabin materials made from these polymers would be ultra-fire-resistant. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Development of an Improved Fire Test Method for Aircraft Ducting Materials This technical report (DOT/FAA/AR-08/4) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in February 2008 and was written by John W. Reinhardt. A comprehensive fire test program was conducted on aircraft ducting materials in an effort to continue mitigating the threat of in-flight fires. Previous work at the Federal Aviation Administration (FAA) William J. Hughes Technical Center has indicated that the current FAA vertical Bunsen burner test requirement could not adequately discriminate between materials that performed poorly and materials that performed well under realistic fire scenarios. From this effort, an alternative radiant heat panel test method was developed. It was demonstrated that this method was effective in evaluating the in-flight fire resistance qualities of aircraft ducting. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Development of Improved Flammability Criteria for Aircraft Thermal Acoustic Insulation This is the full text of a report published by the FAA (Federal Aviation Administration) Fire Safety Section. It was written by Timothy Marker in September 2000. The report number is DOT/FAA/AR-99/44 and it is available in PDF format. Results of in-flight flame propagation tests are reported and discussed. Development of In-Plane Surface Deformation Sensing for Thin Film PVDF Actuated Membrane Mirrors This is the full text of a Master's thesis by Captain John J. Cornelius, USAF, AFIT/GA/ENY/06-M01, which was presented to the Faculty Department of Aeronautical and Astronautical Engineering of Air University's Air Force Institute of Technology (AFIT), in March 2005. This study investigated the feasibility of surface deformation sensing of a membrane mirror using only embedded PVDF sensors. Results were compared to measured deformations using a scanning laser vibrometer. The frequency response function (FRF) was measured based on recorded voltages of a single-layer 7-sensor mirror actuated externally from the embedded PVDF actuators. Additionally, a two-layer, 7-sensor, 7-actuator membrane mirror was constructed for use, with one layer acting as the sensing layer and the other acting as the actuation layer. The measured FRF for this mirror was compared to previous results. Finally a single-layer 61-sensor PVDF mirror was constructed to experimentally investigate the practicality of denser sensor/actuators patterns. Experimental results for all configurations are presented. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC). Directory of organizations, investigators, and programs in high temperature corrosion research This is Research and Technology Organization (RTO) AGARD-R-585, dated August 1971. This directory of research organizations, investigators, and research programs or areas of research was prepared from information gathered by the NATO/AGARD Working Group on Basis and Appied Research on High-Temperature Corrosion, and the European Federation of Corrosion’s Working Group on Corrosion by Hot Gases and Products of Combust ion. There are 178 organizations from eleven NATO countries included. A category index indicates the high-temperature corrosion research areas in which, the various organizations are conducting research. The two research areas currently receiving the most attention are: 1. material behaviour under corrosion and 2. reaction kinetics and diffusion processes, in which 119 and 97 organizations, respectively, are working. An alphabetical index of investigators includes approximately 240 names. The directory lists the organization, together with the investigators and the research areas (or specific programs) in which they are working, alphabetically by countries. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (3.97 MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Effect of Damage on Strength and Durability
This is the full text publication that was assembled to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel (AVT) presented on 17-18 May 2010 in Prague, Czech Republic. This is a report by the Research and Technology Organisation (RTO) of NATO. The author is Mohan M. Ratwani, Ph. D at R-Tec in the USA. Effects of Frequency and Environment on Fatigue Behavior of an Oxide-Oxide Ceramic Matrix Composite at 1200 Deg. C This is the full text of a Master's thesis by Ensign Griffin Hetrick, USN, AFIT/GAE/ENY/06-J05, which was presented to the Faculty Department of Aeronautical and Astronautical Engineering of Air University's Air Force Institute of Technology (AFIT), in June 2006. Advances in aeronautical engineering in the 21st century depend upon materials that can perform well in extreme environments such as high temperatures and oxidizing conditions. Nextel(Trademark)720/Alumina (N720/A) is an oxide/oxide ceramic matrix composite with a porous alumina matrix that has been identified as a candidate material for such applications. This research investigated the effects of frequency on fatigue response of N720/A at 1200C in both air and steam environment. Prior investigation of this material by Eber [8] in 2005 studied fatigue behavior at 1200C in air and in steam environments at the frequency of 1.0 Hz. The current research focused on fatigue response at the frequencies of 0.1 Hz and 10 Hz. Results of mechanical testing showed a significant decrease in fatigue performance in steam versus air. Specimens tested at 0.1 Hz exhibited shorter fatigue lives and smaller strains at failure than those tested at 10 Hz. Scanning Electron Micrographs of specimen fracture surfaces revealed higher degrees of fiber pull-out and greater variation in fiber failure locations in specimens tested at 10 Hz, indicating a weakening of the fiber/matrix interface. Qualitative assessment using Energy Dispersive Spectroscopy showed correlations between frequency and amount of silicon species migration between fiber and matrix. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC). Effects of Hydrogen Peroxide on Common Aviation Textiles This provides access to a Federal Aviation Administration (FAA) Aerospace Medicine Technical Report No.DOT/FAA/AM-09/16 written by S. F. Chou ...[et al] and dated August 2009. Modern transportation systems are subject to unintentional contamination from infected passengers, as well as deliberate contamination from criminals and political adversaries. Hydrogen peroxide has been used for years as a disinfectant in the medical community and is under consideration in the dilute vapor form as a decontaminant/disinfectant/sterilant for transportation vehicles like aircraft, buses, subway trains, ambulances, etc. Although the biological efficacy of STERIS Corporation’s Vaporized Hydrogen Peroxide (VHP® a registered trademark of the STERIS Corporation, Mentor, OH.) technology has been demonstrated elsewhere, the compatibility of the process with typical aircraft materials has not been rigorously established. The present report documents a materials compatibility evaluation involving the effects of hydrogen peroxide exposure on the mechanical properties and flammability of the following commercial-grade textile materials: wool, nylon, polyester, Nomex®, and leather. [Taken from abstract]. The full text is available in PDF format so Adobe Acrobat software is required in order to read it. Electrical Activation Studies of ION Implanted Gallium Nitride This is the full text of a thesis by James A. Fellows which was presented to the Air Force Institute of Technology (AFIT) in 2002. A comprehensive and systematic electrical activation study of Si-implanted gallium nitride (GaN) was performed as a function of ion implantation dose, anneal temperature, and implantation temperature. Additionally, acceptor-implanted GaN was also investigated. Temperature-dependent Hall effect measurements from 10-800 K and photoluminescence (PL) spectra taken from 3-300 K were used to characterize the samples. GaN wafers capped with 500 A1N were implanted at room temperature and at 800 oC with 200 keV Si ions at doses ranging from 1x1013 to 5x1015 cm-2 and annealed from 1050 to 1350 oC for 5 min to 17 sec in a flowing nitrogen environment. Generally, the higher the Si dose, the greater the activation efficiency at any given anneal temperature. The optimum anneal temperature for samples implanted with higher doses (1x1015 cm-2) is around 1350 oC, exhibiting nearly 100% electrical activation efficiency. Even the sample implanted with the lowest dose of 1x1013 cm-2 shows an electrical activation of 40% after annealing at 1350 oC. The mobilities and carrier concentrations increase with anneal temperature for every dose in spite of the increased ionized impurity scattering from an increased number of active donors. The highest room-temperature mobility is 250 cm2/Vs on the sample implanted at room temperature with a dose of 1x1013 cm-2 after annealing at 1350 oC. Even the sample implanted at 800 oC with the highest dose of 5x1015 cm-2 had a room-temperature mobility of 105 cm2/Vs after annealing at 1300 oC. The data show that Si implantation at 800 oC did not offer decisive advantages over implantation at room temperature. PL spectra measured as a function of anneal temperature showed that Si implantation damage was almost completely recovered after annealing at 1350 oC. Also, temperature-dependent PL spectra revealed that the yellow luminescence (YL) plaguing nearly all Si-doped GaN is not caused by a shallow Si donor, but rather a much deeper level. Samples implanted with Si at both room temperature and 800 oC show that the 3.29 eV donor-to-acceptor pair (DAP) peak, which is widely believed to involve a shallow donor, thermally quenches much more rapidly than the 2.2 eV YL band. Additionally, GaN wafers capped with 500 AlN were implanted at 25, 500, and at 800 oC with Mg, Mg+Si, Mg+C, Mg+P, Mg+O, C, Li, and Li+P at doses ranging from 1x1014 to 5x1015 cm-2 and annealed from 1100 to 1350 oC. All of the Mg-implanted and most of the Mg-coimplanted GaN samples became extremely resistive, and did not show definite p-type conductivity even after annealing at 1350 oC. Furthermore, the samples did not show any p-type conductivity and remained highly resistive even at a sample temperature as high as 800 K. A dominant 2.36 eV green luminescence (GL) band observed in the PL spectra of all Mg implanted samples is attributed to a deep DAP transition with at least one level caused by a Mg-related complex. These Mg-related deep complexes, which form independent of the various coimplants or the implantation temperature, remain thermally stable even at anneal temperatures as high as 1350 oC, and are mainly responsible for the inefficient electrical activation of Mg acceptors implanted into GaN. [Taken from abstract]. The full text is available in PDF format and is provided by the Air University ResearchWeb site. Evaluation of Airport Subsurface Materials This provides access to a U.S. Army Corps of Engineers, Cold Regions Research and Engineering Laboratory Special Report 97-13, prepared by Vincent C. Janoo, Robert Eaton, and Lynette Barna, for the Federal Aviation Administration (FAA), dated May 1997. The report describes the examination and testing of eleven sub-surface materials specified by the FAA to determine their susceptibility to frost heave and thaw weakening. The text of the report is available in PDF format (297 K), and is part of the Cold Regions Research and Engineering Laboratory Virtual Library. Evaluation of Fire Test Methods for Aircraft Thermal Acoustical Insulation This final report (DOT/FAA/AR-97/58) was published by the Federal Aviation Administration in September 1997, and was written by Patricia Cahill. It presents the results of laboratory round robin flammability testing performed on thermal acoustical insulation blankets and the films used as insulation coverings. This work was requested by the aircraft industry as a result of actual accidents involving flame propagation on the thermal acoustical blankets. Vertical flammability testing was performed as specified in Federal Aviation Regulation (FAR) 25.853, Appendix F. In addition, a cotton swab test developed by aircraft manufacturers was also evaluated [extracted from the Executive Summary]. This is a PDF file [23 pages, 82k] so Adobe Acrobat software will be required in order to read it. Evaluation of Reciprocating Aircraft Engines With Unleaded Fuels : Final Report This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-99/70, by David H. Atwood and Kenneth J. Knopp, dated December 1999. This report examines the development of an unleaded fuel for use by the general aviation community. The focus of the study is on the determination of the minimum motor octane number required for knock free operation of the majority of the piston engine fleet. Data from both ground based engine testing and in-flight testing are included.The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library. Evaluation of Thermoplastic Marking Materials This provides access to a Federal Aviation Administration (FAA) Report No.DOT/FAA/AR-TN08/22 written by Holly Cyrus and Anthony Previti dated Mat 2008. Due to the harsh conditions of airport environments, frequent repainting of existing waterborne pavement markings is required. This painting is expensive and affects life-cycle costs. A thermoplastic marking material has been identified as an alternative to the existing waterborne material. The purpose of this research effort was to determine if this thermoplastic marking material is as effective as the current waterborne material in terms of its retro-reflectivity, chromaticity, friction properties, and its adherence to the airport pavement surface. Two types of thermoplastic materials were applied on asphalt and concrete surfaces at the Federal Aviation Administration William J. Hughes Technical Center and were evaluated for 1 year starting in June 2006. These materials were also applied on concrete pavement surfaces at the Newark Liberty International Airport and evaluated for 1 year starting in August 2006. One thermoplastic material was 60-mil thick with Type I and III beads and was applied on a heated surface; the other material was 90-mil thick with Type I and IV beads and was applied on cold surface. Retro-reflectivity was measured using a retro-reflectometer; a spectrophotometer was used to measure chromaticity, a Dyna-Meter Pull-Off tester was used to measure adherence strength, and a Saab Surface Friction Tester was used to measure friction properties. Most measurements were taken on a monthly basis. The results showed that the retro-reflectivity characteristics of thermoplastic marking materials were acceptable. The chromaticity of the thermoplastic was within tolerance for white, red, yellow, and black. The average friction readings recorded on thermoplastic were significantly lower than those taken on bare pavement and about 50% less than waterborne paint. The adherence showed that preparation is necessary for a good bond. The tensile strength of the bond between the thermoplastic marking material and hot-mix asphalt was acceptable. The tensile strength of the bond between the thermoplastic marking material and Portland cement concrete was acceptable when an additional adhesive was applied. Based on the result of this evaluation, thermoplastic marking material is recommended for taxiways. [Taken from abstract]. The full text is available in PDF format so Adobe Acrobat software is required in order to read it. Extension of Viscoplasticity Based on Overstress to Capture the Effects of Prior Aging on the Time Dependent Deformation Behavior of a High-Temperature Polymer: Experiments and Modeling This is the full text of a thesis written by Amber McClung which was presented to the Air Force Institute of Technology, Wright Patterson Air Force Base, Ohio, in October 2008. The inelastic deformation behavior of PMR-15 neat resin, a high-temperature thermoset polymer, was investigated at 288 degrees C. The experimental program was designed to explore the influence of strain rate on tensile loading, unloading, and strain recovery behaviors. In addition, the effect of the prior strain rate on the relaxation response of the material, as well as on the creep behavior following strain controlled loading were examined. The experimental data were modeled with the Viscoplasticity Based on Overstress (VBO) theory. A systematic procedure for determining model parameters was developed and the model was employed to predict the response of the material under various test histories. Additionally the effects of prior aging at 288 degrees C in argon on the time (rate)-dependent behavior of the PMR-15 polymer were evaluated in a series of strain and load controlled experiments. Based on experimental results, the VBO theory was extended to capture the environmentally induced changes in the material response. Several of the VBO material parameters were expanded as functions of prior aging time. The resulting model was used to predict the high-temperature behavior of the PMR-15 polymer subjected to prior aging of various durations. [Taken from Abstract]. This is in PDF format so Adobe Acrobat software is required in order to read it. FAA Finite Element Design Procedure for Rigid Pavements This technical report (DOT/FAA/AR-07/33) was produced by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in August 2007 and was written by Edward Guo, Lia Ricalde and Izydor Kawa. FEDFAA, Finite Element Design—Federal Aviation Administration, is a computer program for both airport rigid and flexible pavement thickness design. NIKE3D (a general-purpose, three-dimensional finite element method (3D-FEM) computer program) is the selected engine for critical stress calculation for airport rigid pavement design. The calculated edge stresses are used in the FEDFAA failure model to determine the slab thickness. Since FEDFAA is a tool for thickness design rather than for analysis, certain program modifications and selection of available elements in NIKE3D have been made during FEDFAA development; it includes (1) selection of the nonconforming eight-node solid element to model all layers of the pavement except the subgrade, (2) introduction of the infinite element to model the infinitely deep subgrade, (3) mesh densities in vertical and horizontal directions, and (4) slab size and width of subbase extension have been determined to fit the needs of the design. A procedure has also been developed to calculate the critical stress of the pavement from the stresses calculated by NIKE3D at the element Gaussian points. Finally, the modified 3D finite element-based program was evaluated by using three criteria: (1) the model must be theoretically correct; (2) the final stress calculation engine with modifications and simplifications provides critical stress close enough to the precise one; and (3) it should be able to complete this computation under aircraft load within a few minutes. This report provides detailed descriptions for model selections, program modifications, and numerical evaluations. The report concludes that the final tool satisfies all three criteria; therefore, it is a reliable and applicable tool for airport rigid pavement design. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Fabrication Techniques for III-V Micro-Opto-Electro-Mechanical Systems This is the full text of a thesis by Jeremy A. Raley which was presented to tThis thesis studies techniques for selective removal of semiconductor material in AlxGa1xAs systems for the purpose of fabricating Micro-Opto-Electro-Mechanical Systems (MOEMS). Fabrication in AlxGa1xAs allows for the emission, control, and detection of light from the near-infrared to the visible region of the spectrum. Specifically, MOEMS will enable wavelength division multiplexing (WDM) in the next generations of communications equipment, which will multiply the amount of information that can be sent through existing optical fiber cabling. This work was accomplished by performing an etch study on the selective removal of GaAs from an AlxGa1xAs structure. The technique of oxidizing AlAs or Al0:98Ga0:02As and removing the oxide was also investigated along with methods for the direct removal of AlAs. The knowledge gained during these etch studies was then applied to the fabrication of Micro-Electro-Mechanical tunable Fabry-Perot filters as well as lift-of microcavity light emitting devices. The etchants and materials studied showed high selectivity for removal of both GaAs and AlAs. Mechanical structures were fabricated and actuated using these techniques and resonant cavity light emitting diodes were transplanted from their native substrate to another substrate singly and in arrays. This thesis presents three methods for fabricating MEM systems in III-V materials. This fabrication knowledge will be applied to the fabrication of devices such as tunable vertical cavity surface emitting lasers (VCSELs). Transplantable optical devices have broad applications in the areas of computing and communications. This work can also be used as a basis for fabrication of Nano-Electro-Mechanical Systems using crystalline III-V materials. he Air Force Institute of Technology (AFIT) in 2002. [Taken from abstract]. The full text is available in PDF format and is provided by the Air University ResearchWeb site. Fire- and Smoke-Resistant Interior Materials This web site provides access to the full text of: Fire- and Smoke-Resistant Interior Materials for Commercial Transport Aircraft, by the Committee on Fire and Smoke Resistant Materials for Commercial Aircraft Interiors, National Research Council, 1996. The two principal objectives of this study were: to identify promising materials technologies, design issues (both overall and for individual components) and fire performance parameters (both full scale and for individual components) that, if properly optimized, would lead to improved fire and smoke resistance of materials and components used in aircraft interiors; and to identify long-range research directions that hold the most promise for producing predictive modeling capability, new advanced materials and the required product development to achieve totally fire-resistant interiors in future aircrafts. The text is available online in Open Book format. There is also an executive summary in HTML format. Fire-Resistant Elastomers This is a Federal Aviation Administration (FAA) report, DOT/FAA/AR-TN01/104, by Richard E. Lyon, dated May 2002. Molecular design of semi-inorganic rubbers has yielded flexible polysilphenylene-siloxane and polyphosphazene elastomers having the fire resistance of rigid, high-temperature engineering plastics (e.g., polyaramids, polyetherketones, and polyarylsulfones) based on the results of microscale combustibility data. In flaming combustion, a commercially viable polyphosphazene exhibited a 75% reduction in heat release rate compared to the polyurethane rubber currently used in fire-blocked foam aircraft seat cushions. A comparable reduction in heat release rate is obtained at lower cost by adding expandable graphite flakes to the polyurethane formulation. The graphite flakes exfoliate during heating to produce a 2000% volumetric expansion of the burned rubber which shields and insulates the underlying material from the heat source and lowers the heat release rate significantly. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library. Fire-Resistant Materials : Research overview This final report (DOT/FAA/AR-97/99) was published by the Federal Aviation Administration (FAA) in December 1997, and was written by Richard E. Lyon. It provides an overview of the research being conducted by the FAA to develop fire safe cabin materials for commercial aircraft. The objective of the Fire-Resistant Materials program is to eliminate burning cabin materials as a cause of death in aircraft accidents. Long-term activities include the synthesis of new, thermally stable, low fuel value organic and inorganic polymer systems. The synthesis effort is supported by fundamental research to understand polymer combustion and fire resistance mechanisms using numerical and analytical modeling and the development of new characterization techniques [extracted from author abstract]. This is a PDF file so Adobe Acrobat software will be required in order to read it. Fire-Safe Polymers and Polymer Composites This technical report (DOT/FAA/AR-04/11) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in September 2004 and was written by Huiqing Zhang. The intrinsic relationships between polymer structure, composition, and fire behavior have been explored to develop new fire-safe polymeric materials. Three milligram-scale methods (pyrolysis-combustion flow calorimetry (PCFC), simultaneous thermal analysis, and pyrolysis gas chromatography/mass spectrometry (GC/MS)) have been combined to fully characterize the thermal decomposition and flammability of polymers and polymer composites. Thermal stability, mass loss rate, char yield, and properties of decomposition volatiles were found to be the most important parameters in determining polymer flammability. Most polymers decompose by either an unzipping or a random chain scission mechanism with an endothermic decomposition of 100-900 J/g. Aromatic or heteroaromatic rings, conjugated double or triple bonds, and heteroatoms such as halogens, N, O, S, P, and Si, are the basic structural units for fire-resistant polymers. The flammability of polymers can also be successfully estimated by combining the pyrolysis GC/MS results or chemical structures with the thermogravimetric analysis. The thermal decomposition and flammability of two groups of inherently fire-resistant polymerspoly(hydroxyamide) (PHA) and its derivatives and bisphenol C (BPC II) polyarylateshave been systematically studied. PHA and most of its derivatives have extremely low heat release rates and very high char yields upon combustion. PHA and its halogen derivatives can completely cyclize into quasi-polybenzoxazole structures at low temperatures. However, the methoxy and phosphate derivatives show a very different behavior during decomposition and combustion. Molecular modeling shows that the formation of an enol intermediate is the rate-determining step in the thermal cyclization of PHA. BPC II-polyarylate is another extremely flame-resistant polymer. It can be used as an efficient flame-retardant agent in copolymers and blends. From the PCFC results, the total heat of combustion of these copolymers or blends changes linearly with composition, but the change of maximum heat release rates also depends on the chemical structure of the components. The flammability of various polymers and polymer composites measured by PCFC; cone calorimeter, ASTM E1354; and the Ohio State University (OSU) calorimeter, ASTM E906, were also compared. For pure polymers, there was a relatively good correlation between different methods. However, for polymer composites with inert fillers or flame-retardant additives, the OSU and cone calorimetries are more suitable evaluation methods. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Fire-Smart DDE Polymers This technical report (DOT/FAA/AR-06/12) was produced by the Federal Aviation Administration (FAA) Office of Aviation Research in April 2006 and was written by Richard E. Lyon, Louise Speitel, Robert Filipczak, Richard Walters, Sean Crowley, Stanislav Stoliarov, Lauren Castelli and Michael Ramirez. The chemistry and properties of polymers containing the fire-smart moiety 1,1-dichloro-2,2-diphenylethene (DDE) are described. These polymers are typically derived from the bisphenol of chloral and are low-cost, easily processed, and have good mechanical properties and toughness under normal conditions. Under fire conditions, the DDE group undergoes an intramolecular rearrangement to diphenylethynyl with the elimination of hydrogen chloride (a noncombustible gas) and intermolecular crosslinking to form an aromatic char residue in high yield. The flammability and mechanical properties of DDE-containing polymers are described. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Flammability Characteristics of TKS Anti-Icing Fluid This technical report (DOT/FAA/AR-TN08/9) was published by the Federal Aviation Administration (FAA) Office of Aviation Research in January 2008 and was written by William M. Cavage. TKS anti-icing fluid is being used in a variety of platforms to provided anti-/deicing capability for smaller commercial aircraft. The flammable liquid is comprised of 85 percent ethylene glycol, 10 percent water, and 5 percent isopropyl alcohol, andquestions about its potential hazards have been raised. These hazards include, but are not limited to, the heating of small puddles of fluid that were either spilled or leaked, dripping of the fluid on hot surfaces, and the contact of the fluid mist with ignition sources. Simple tests were performed to allow for a more basic characterization of the TKS anti-icing fluid flammability. These tests were (1) an ASTM D 56-87 flash point test, (2) a hot-pan flammability test, (3) a hot-surface ignition test, and (4) a spray flammability test. As expected, TKS anti-icing fluid is flammable under the correct conditions. The flash point was found to be approximately 150°F, but the fluid appears to have a very low energy release when reacting. The fluid will burn if heated in a pan to approximately 250°F and subjected to an ignition source, but burns relatively cool. When dripped onto a hot surface, the fluid does not react but will probably display relatively violent characteristics if heated in a confined space above 750°F (approximate autoignition temperature). The fluid will burn in a mist at ambient temperature and pressure when exposed to a flame, but will not sustain a reaction when the flaming ignition source is removed. Only sporadic ignitions (no fireball) confined to small areas were observed when the mist was ignited with a spark. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software is required in order to read it. Flammability of Automotive Child Restraint Seats for Use in Aircraft This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-TN01/42, by Richard Johnson and Lindsey Wuethrich, dated November 2001. Child restraint seat used in aircraft are based on automotive designs that are required to pass a horizontal burn rate test method. The flammability of child seat materials was gauged against the Federal Aviation Administration (FAA) vertical Bunsen burner tests method. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library. Flammability of Epoxy Resins Containing Phosphorus This technical report (DOT/FAA/AR-TN05/44) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in November 2005 and was written by Paul M. Hergenrother, Craig M. Thompson, Joseph G. Smith Jr., John W. Connell, Jeffrey A. Hinkley, Richard E. Lyon, and Richard Moulton. As part of a program to develop fire-resistant exterior composite structures for future subsonic commercial and general aviation aircraft, flame-retardant epoxy resins are under investigation. Epoxies and their curing agents (aromatic diamines) containing phosphorus were synthesized and used to prepare epoxy formulations. Phosphorus was incorporated within the backbone of the epoxy resin and not used as an additive. The resulting cured neat epoxy formulations were characterized by thermogravimetric analysis, propane torch test, elemental analysis, microscale combustion calorimetry, and fire calorimetry. Several formulations showed excellent flame retardation with phosphorous contents as low as 1.5% by weight. The fracture toughness and compressive strength of several cured formulations showed no detrimental effect due to phosphorus content. The chemistry and properties of these new epoxy formulations are discussed. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software is required in order to read it. Flammability Properties of Clay-Nylon Nanocomposites This technical report (DOT/FAA/AR-07/29) was produced by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in June 2007 and was written by Xin Liu and J.G. Quintiere. The flammability properties of nylon samples with different percentages of clay dispersed on the nanometer (molecular) scale were measured by a fire (cone) calorimeter. Specifically, chemical energy release rate, mass loss rate, and time to ignite (melt and char) were measured. This study consisted of samples of pure Nylon 6 and nylon that contained nanoclay additives at 2% and 5% by weight. In addition, the effect of sample thickness was considered for 1.6 to 24 mm. Data obtained over a range of radiant heat flux (17 to 55 kW/m2) were analyzed to illustrate the effect of sample clay loading and thickness on heat of combustion, heat of gasification, and ignition temperature. The findings indicated that the heats of combustion based on mass loss did not change with clay loading, and were 28 ±1 kJ/g. The critical heat flux for ignition did not appear to be influenced by the clay additive; it decreased from 17.7 for pure nylon to 16.0 with 5% clay addition. These values correspond roughly to an ignition temperature of 430° C, compared to a decomposition temperature range from a thermogravimetric analyzer of 350° to 430°C. However, the addition of the clay could increase the ignition time by 30% to 100% over the pure nylon. This is believed to be due to the increased char residue and the decrease in the mass loss rate. The char-like residue yield was nearly identical to the clay loadings. The overall average mass loss rate was reduced by up to 50% with a 5% clay composition over pure nylon for a given heat flux and thickness. For the clay nanocomposites, the burning rate increased as the thickness decreased. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Full-Scale Tests of Lightweight Fragment Barriers on Commercial Aircraft : Final Report This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-99/71, by Donald A. Shockey, David C. Elrich, and Jeffrey W. Simmons, dated November 1999. The report is part of an investigation of the ballistic effectiveness of fabric structures. It describes a series of tests to determine the effects of polymer material, number of plies, location of the fabric within the fuselage wall, and gripping arrangements. The results confirmed that high-strength polymer fabrics offer an extremely effective, low-weight solution for mitigating the effects of uncontained turbine engine fragments on commercial aircraft. The full text of the report is available in PDF format from the online catalogue of the FAA William J. Hughes Technical Center Library. Heat Release and Flammability Testing of Surrogate Panels This technical report (DOT/FAA/AR-TN01/112) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in December 2001 and was written by Timothy Marker. A task group assembled under the auspices of the International Aircraft Materials Fire Test Working Group examined issues involving fire test approval of previously qualified interior material systems following renovation or alteration. A major problem associated with the alteration of interior system components is the difficulty in conducting certification tests that would determine if the altered interior component is still compliant with the heat release, smoke, and flammability certification requirements. [Taken from abstract] This is a PDF file, so Adobe Acrobat software will be required in order to read it. Heats of Combustion of Brominated Epoxies This technical report (DOT/FAA/AR-TN05/45) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in November 2005 and was written by Stanislav I. Stoliarov, Qaadir Williams, Richard N. Walters, Sean Crowley and Richard E. Lyon. The widespread use of brominated flame retardants and fire extinguishing agents in aircraft cabins and recent concerns about their combustion toxicity and environmental impact prompted a study to understand the mechanism by which bromine inhibits the flaming combustion of plastics as a first step towards identifying alternative chemicals or compounds. The heats of combustion of bromine-containing epoxies were calculated from the known atomic composition and compared to measured values in flaming and nonflaming combustion. The heat of flaming combustion was measured in a fire/cone calorimeter (CC) and by burning pyrolysis products in a methane laminar diffusion flame (pyrolysis-flaming combustion calorimetry (PFCC)). Heats of nonflaming combustion were measured by pyrolysis-combustion flow calorimetry (PCFC). The results of these tests indicate that the combustion heat released by these materials decreases with increasing amounts of brominated components as a result of incomplete combustion, char formation, and dilution of the materials with noncombustible bromine. Gas-phase combustion efficiency in the various test methods decreased as: PCFC > PFCC > CC. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software is required in order to read it. Hexavalent Chromium Dissociation from Overspray Particles into Fluid for Three Aircraft Primers This is the full text of a thesis by Richard Schilke which was presented to the Air Force Institute of Technology (AFIT) in 2002. The Department of Defense and industry use chromate-containing primer paints extensively to inhibit corrosion on metal assets. Chromate, a primer pigment, provides excellent corrosion inhibition, but contains hexavalent chromium (Cr6+), a human carcinogen. There is no reliable epidemiological evidence of increased lung cancer incidence among painters potentially exposed to primer overspray particles. Using ioaerosol impingers, overspray particles from three different primers (solvent-borne epoxy, water-borne epoxy, and solvent-borne polyurethane) were collected into water to test the hypothesis that the paint matrix influences Cr6+ release into water. This collection method is intended to simulate Cr6+ release from paint particles into lung fluid. Collected particles were allowed to reside in the water for 1 and 24 hours after which the particles were separated from the water by centrifugation. Supernatant water was then tested for dissolved [Cr6+]. The mean fractions of Cr6+ released into the water after 1 and 24 hours for each primer (95% confidence) were: 70 + 5% and 85 + ?5% (solvent epoxy), 74 + ?4% and 84 + ?4% (water epoxy), and 94 + 3% and 95 + 2% (polyurethane). The epoxy primers demonstrated a range of 24-hour Cr6+ release from complete (100%) dissociation to as low as 33% for the solvent epoxy, and 48% for the water epoxy. Correlations between the distribution of Cr6+ with particle size and % Cr6+ dissociated from each sample indicate that particles < 5 m release a larger fraction of their Cr6+ during the first 24 hours versus particles > 5 m. [Taken from abstract]. The full text of the thesis is avialable in PDF format and is provided by the Air University ResearchWeb site. High Temperature Degradation of 5250-4 Polymer Resin This is the full text of a thesis by Patrick E. Link which was presented to the Air Force Institute of Technology, Wright Patterson Air Force Base, Ohio in June 2007. 5250-4 bismaleimide resin is used in high performance polymer matrix composites with high temperature aeronautical applications. This thesis investigated the thermal and oxidative degradation of 5250-4 neat resin powder in argon, air, and oxygen environments. The powder was aged at 163⁰C, 177 ⁰C, and 190⁰C in all environments for at least 250 hours. Isothermal thermo-gravimetric analysis demonstrated that weight loss was negligible for aging in the argon environment, indicating weight loss is the result of an oxidative process at these temperatures. The 5250-4 powder exhibited an initial period of weight gain before eventually losing weight in both air and oxygen. The applicability of a closed loop oxidation scheme to 5250-4 gravimetric behavior wasinvestigated. Kinetic parameters for the scheme were determined for the Air Force Research Laboratory’s polymer matrix composite lifetime prediction modeling efforts. [Taken from abstract]. The full text of the thesis is available in PDF format so Adobe Acrobat software is required in order to read it. History, Processing, and Usage of Recycled Glycol for Aircraft Deicing and Anti-Icing : Final Report This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-00/55, by Max Kurowski, dated February 2001. The primary objective of this study was to globally investigate and document spent glycol recycling methods and practices, including Asian, former Soviet bloc countries, and other areas of the world not within the purview of current SAE/ISO fluid standards. The findings of the study provide information relevant to the establishment of an on-site or remote glycol recycling facility, what can be expected from such a facility, the utilisation of the refined glycol, and a method for reprocessing into aircraft deicing/anti-icing fluid. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library. Impact of Acoustic Loads on Aircraft Structures This is Research and Technology Organization (RTO) AGARD-CP-549, dated September 1994. A broad band of different activities was addressed in the Specialists' Meeting held by the Structures and Materials Panel of AGARD in May 1. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (152.88MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Improved Barriers to Turbine Engine Fragments : Interim Report I This web site provides access to a Federal Aviation Administration Report titled: Improved Barriers to Turbine Engine Fragments: Interim Report I, by D.A. Shockey, Jeffrey W. Simmons and David C. Elrich, DOT/FAA/AR-99/8, June 1999. This is the first part of a report produced by SRI International's Poulter Laboratory on behalf of the FAA, which examines the ballistic performance of various barriers of Zylon (polybenzoxazole, PBO) fabric, in gas gun tests using fragment simulating projectiles. The framework of a fabric model was constructed and simple impacts were simulated to demonstrate efficacy. The full text of the report is available in PDF [10.0 Mb] format from the online catalogue of the FAA William J. Hughes Technical Center Library. Improved Barriers to Turbine Engine Fragments : Interim Report II This web site provides access to a Federal Aviation Administration (FAA) Report titled: Improved Barriers to Turbine Engine Fragments: Interim Report II, by D.A. Shockey, Jeffrey W. Simmons and David C. Erlich, DOT/FAA/AR-99/8, II, May 1999. The is the second part of a report produced by SRI International's Poulter Laboratory on behalf of the FAA, which evaluates the ballistic effectiveness of fabric structures made from advanced polymers, and investigates the computational modeling of fragment barriers. The ballistic response of fabrics to fragment impact was evaluated, the phenomenology of fabric deformation and failure was elucidated in quasi-static penetration tests, and the tensile properties of yarns and fibers were measured. The full text of the report is available in PDF [1.2 Mb] format from the online catalogue of the FAA William J. Hughes Technical Center Library. Improved Barriers to Turbine Engine Fragments : Interim Report III This web site provides access to a Federal Aviation Administration (FAA) Report, by D.A. Shockey, David C. Elrich, and Jeffrey W. Simmons, DOT/FAA/AR-99/8, III, May 2001. The report describes the development of a mathematical model to assist the efficient design of fabric fragment barriers. The model was used to simulate the failure behaviour of yarns and fabrics under impact scenarios. The full text of the report is available online in PDF format. Indoor Snow Testing of Aircraft Ground Anti-Icing Fluids This technical report (DOT/FAA/AR-06/14) was published by Federal Aviation Administration (FAA) Office of Aviation Research in April 2006 and was written by Arlene Beisswenger and Jean Perron. Currently, holdover time performance for aircraft deicing and anti-icing fluids under snow conditions are determined from outdoor tests on flat plates in natural snow. The Federal Aviation Administration Airport and Aircraft Safety Research and Development Division has sponsored research to do similar tests under indoor laboratory conditions. Such indoor tests would lead to a more timely and improved assessment of a new fluid’s performance without relying on outdoor snow conditions. During past investigations, when similar tests were conducted in laboratory cold rooms, the resulting holdover times were significantly different (typically shorter) from those produced outdoors in natural snow conditions. This difference was attributed to the effects of wind. Recent research at the National Center for Atmospheric Research has produced indoor procedures using temperature-controlled test plates that accounted for the effects of wind and produced holdover time results that more closely matched those obtained from outdoor snow tests. The first objective of this current effort was to participate in round-robin tests with two other organizations, using prior outdoor results from many certified fluids for different snow intensities and temperatures. The results from this effort indicated that the data from the three test organizations/sites correlated well with results obtained from measurements in outdoor natural snow conditions. Next, the improved procedure was used to obtain holdover time performance for fluids at -25°C for snow conditions. This was performed since existing holdover time values had been based upon theoretical mathematical extrapolations, or for some new fluids. These values were assigned based upon existing worst-case values at this temperature. The results indicated that the measured laboratory values typically exhibited holdover time values shorter than those obtained from the mathematical extrapolations for a temperature range of -14° to -25°C. An additional objective of this effort was to develop and evaluate a more objective fluid failure call procedure, in lieu of the current criteria, in which fluid failure is based upon the condition when 30% of the test plate is covered with snow. Conceivably,the 30% snow coverage failure call criteria can be imprecise since it relies upon human observations. Previously, it was noted that the fluid extracts heat from the surroundings for the energy required to absorb the snow. When the snow is no longer being absorbed by the fluid, the fluid is no longer draining thermal energy, and the fluid has failed. During this investigation, the amount of heat required by the system to maintain the required plate temperature was recorded, and by observing changes in this value, it was determined that an objective fluid failure call based upon this criteria was very promising. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Inerting Conditions for Aircraft Fuel Tanks This technical report (WADC/TR/55-418) was produced by the Wright Air Development Center (WADC) in September 1955 and was written by Paul B. Stewart and Ernest S. Starkman. Determination of the flamability limits of aircraft fuel as a function of pressure, type of fuel, temperature and ignition energy was the purpose of this investigation. The investigation was conducted in chambers ranging from 8 to 12.5 cubic feet to determine applicability of small scale Laboratory data to aircraft fuel tanks. The data obtained from a capacitor discharge spark ignition source was correlated with similar data obtained using incendiary ammunition as the ignition source. The latter data was obtained at sea level pressure. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software is required in order to read it. Investigating the Thin-Film Versus Bulk Material Properties of Structural Adhesives This provides access to a Federal Aviation Administration (FAA) technical report DOT/FAA/AR-06/45 written by Nicholas Burst and Daniel O. Adams dated May 2008. A combined experimental and computational investigation was performed to determine whether the material properties of structural adhesives differ between their thin-film in situ and bulk forms. Both shear and tensile tests were performed using bulk adhesive specimens as well as in situ adhesive specimens. Three aerospace-grade adhesives were used: Loctite EA 9394, EA 9392, and EA 9360. For in situ adhesive tests, three bondline thicknesses of 0.25 mm (0.01 in.), 1.27 mm (0.05 in.), and 2.54 mm (0.10 in.) were investigated. Shear tests focused on the use of the V-notched Iosipescu shear specimen, featuring a 120° notch angle for use with thin adhesive bondlines. Additionally, the thick adherend lap joint test configuration was evaluated for determining shear properties of adhesives. Tensile tests focused on adhesively bonded butt joint specimens as well as bulk adhesive bar specimens. The results from in situ and bulk adhesive shear tests suggest that the slight decrease in apparent shear strength with increasing bondline thickness was produced by slight changes in the adhesive stress state. Further, the shear strengths obtained from bulk adhesive tests were comparable to those from in situ tests. The results from moiré interferometry showed that no significant difference in adhesive shear modulus between the three thicknesses investigated. Combined, these results suggest that the shear strength and shear modulus of the adhesives investigated do not differ when tested in their thin-film in situ and bulk forms. Additionally, these results show that the Iosipescu shear test configuration is well suited for both in situ and bulk adhesive shear tests. Finite element analyses and moiré interferometry experiments performed for the thick adherend lap shear test showed a relatively nonuniform state of stress throughout the adhesive bondline, suggesting that the test results may not be representative of the actual adhesive shear properties. The results from butt tensile tests and analysis suggest that the apparent variation in tensile strength as a function of bondline thickness was a result of variations in the adhesive stress state, rather than the actual tensile strength of the adhesive. In total, the results of this investigation suggest that the adhesive properties obtained from bulk adhesive specimens are valid for use in structural analysis of in situ thin-film adhesives. [Taken from abstrct]. The full text is available in PDF format so Adobe Acrobat software is required in order to read it. Investigation of a New Formulation Reference Fluid for use in Aerodynamic Acceptance Evaluation of Aircraft Ground Deicing and Anti-icing Fluids This technical report (DOT/FAA/AR-06/50) was produced by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in May 2007 and was written by Arlene Beisswenger, Jean-Louis Laforte, Marc-Mario Trenblay and Jean Perron. A new formulation fluid is proposed for use as the reference fluid for aerodynamic testing and qualification of commercial aircraft deicing and anti-icing fluids. The new formulation fluid is to replace the currently used reference fluid, MIL-A-8243D, which allows for large variation in its composition. The MIL-A-8243D fluid, manufactured up to 2005, is no longer commercially available because its chief user, the United States Military, now uses qualified commercial Society of Automotive Engineers deicing and anti-icing fluids. The new formulation fluid, a mixture of 68% propylene, 20% tripropylene glycol, and 12% demineralized water, is chemically compatible with current glycol-based fluids. Furthermore, it can be produced more simply and accurately than the more complex military (MIL) formulation it replaces. Having the same viscosity as MIL-A-8243D, the new formulation reference has been found to be essentially aerodynamically indistinguishable from the MIL fluid in validation test runs in which both fluids were tested with a candidate fluid for high-speed ramp aerodynamic standard qualification. The measurements and validation testing accomplished in the present study support the adoption of the new fluid for use as the reference fluid for the high-speed ramp standard aerodynamic qualification test in place of the current MIL fluid. An investigation similar to the one described in this report could establish if the new fluid also can be used as the reference fluid for the low-speed ramp standard aerodynamic qualification test. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Italian Aerospace Research Centre This is the homepage of the Italian Aerospace Research Centre (CIRA), a non-profit making research consortium which carries out the Italian National Aerospace Research Programme (PRORA). The site gives an introduction to the organisation and the scientific and the educational areas covered. It describes CIRA's aerospace activities (which include fluid dynamics, air structures, flight systems and computer science) and testing facilities (which include a plasma wind tunnel, an icing wind tunnel, a transonic research wind tunnel and an aerospace structures impact facility. The projects area of the site describes work being carried out on unmanned aerial vehicles and unmanned space vehicles. The educational area covers topics such as flight safety, pssengers comfort, air transportation and access to space. The general support area provides access to the Library Catalogue. The CIRA Newsletter is also available. Jet A Volatility Survey This technical report (DOT/FAA/AR-07/30) was produced by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in July 2007 and was written by Skip Byrnes. In response to the July 1996 TWA Flight 800 disaster, the Federal Aviation Administration (FAA) collected jet fuel samples from domestic and international flights to determine the actual flash point of jet fuel in service. This data was collected tohelp determine whether any change in the ASTM D1655 turbine fuel specification would help prevent any future such incident and to use in fuel tank flammability assessments. This report details the flash point results from 293 jet fuel samples collected from April 1998 through September 1999. The results found no fuel samples to be out of specification. Samples were retrieved at the end of flights, before refueling, that ended in Philadelphia, PA; New York, NY (JFK); and Newark, NJ. These locations provided convenient locations for FAA technicians to be able to obtain samples from fuel from all over the US and abroad. The results helped determine that no change in the turbine fuel specification was required. The flashpoint distribution from the survey was also used in the harmonized FAA special conditions issued for the B-747 and B-737 fuel tank flammability reduction means and in the proposed Title 14 Code of Federal Regulations Part 25 Appendix L that was published in the Notice of Proposed Rulemaking titled, "Reduction of Fuel Tank Flammability in Transport Category Airplanes" (docket number FAA-2005-22997). [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Laboratory-Scale and Full-Scale Fire Testing of Lightweight Aircraft Seat Cushion Materials This technical report (DOT/FAA/AR-06/49) was produced by the Federal Aviation Administration (FAA) in March 2007 and was written by Timothy R. Marker. Laboratory- and full-scale fire tests were conducted on a number of different types of aircraft seat cushion materials to determine the applicability of the current weight loss criteria specified in Title 14 Code of Federal Regulations Part 25.853(c) Appendix F Part II (herein referred to as Appendix F Part II) to new, very lightweight cushion designs. Cushion samples were initially tested in accordance with the current standard, and if they exceeded the 10% weight loss criteria, they were evaluated under full-scale fire test conditions. The full-scale tests were conducted with a modified narrow-body fuselage test article exposed to an adjacent fuel pan fire to simulate a severe but survivable postimpact cabin fire. Four triple-seat frames used to mount the cushion samples were installed inside the test article. Aircraft-grade honeycomb sidewall, ceiling panels, and carpet were also installed in the vicinity of the seat frames to simulate a realistic aircraft cabin. Laboratory-scale tests were completed on one set of standard fire-blocked cushions that met the current Appendix F Part II requirement, in addition to four lightweight materials. The standard fire-blocked cushions were then run under full-scale conditions to provide a baseline of the current level of fire safety, followed by full-scale tests of the four lightweight materials. Results indicated that several of the lightweight seat materials that failed the weight loss criteria specified in Appendix F Part II did not result in greater fire hazards than the baseline materials when tested under realistic full-scale conditions. A conservative adjustment to the current weight loss criteria was developed to allow the use of very lightweight seat cushion materials that exhibit acceptable fire performance. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Materials Safety Data Sheets This web site provides access to a large, searchable archive of Materials Safety Data Sheets (MSDS). It includes links to many new MSDS archives provided by manufacturers concerned about the safe use of their products. The archive contains details of hazardous materials used in the aerospace industry - eg lubricants, coatings, cleaning compounds etc. The whole MSDS archive can be downloaded. The site also features a searchable database of toxicology reports, which can be accessed by entering a chemical name, or the CAS or RTECS number. Modal Approach 2003 Quantum Mechanical Calculations of Monoxides of Silicon Carbide Molecules This is the full text of a thesis by John W. Roberts, Jr. which was presented to the Air Force Institute of Technology (AFIT) in 2003. Modern semiconductor devices are principally made using the element silicon. In recent years, silicon carbide (SiC), with its wide band-gap, high thermal conductivity, and radiation resistance, has shown prospects as a semiconductor material for use in high temperature and radiation environments such as jet engines and satellites. A limiting factor in the performance of many SiC semiconductor components is the presence of lattice defects formed at oxide dielectric junctions during processing. Recent theoretical work has used small quantum mechanical systems embedded in larger molecular mechanics structures to attempt to better understand SiC surfaces and bulk materials and their oxidation. This research uses quantum mechanical models to calculate geometries and electronic properties of small SimCnO molecular clusters of silicon carbide oxides with SimCnO, 4. Calculations are primarily done using Hartree-Fock and Density Functional Theory (DFT) with the B3LYP exchange and correlation functionals. Mller-Plesset Second Order Perturbation (MP2), Configuration Interaction (CI), Multi-Configurational Self-Consistent Field (MCSCF), and Coupled Cluster (CC) are used on the CSi2O molecule to confirm the accuracy of selected levels of DFT. Molecular properties examined include ground state multiplicity, vibrational modes and frequencies, and geometry for both the neutral and anion, adiabatic and vertical electron affinities, and thermodynamic heats of formation. Qualitative predictions are made regarding the photoelectron spectrum experimentalists may see. Finally, preferred geometries, functional groups, and bonding locations are qualitatively determined. Later research will be able to use these results to study the oxidation of larger SiC structures and surfaces and their defects. [Taken from abstract]. The full text of the thesis is available in PF format and is provided by the Air University ResearchWeb site. Molecular Modeling of the Thermal Decomposition of Polymers This technical report (DOT/FAA/AR-05/32) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in October 2005 and was written by Stanislav I. Stoliarov, Phillip R. Westmoreland, Huiqing Zhang, Richard E. Lyon, and Marc R. Nyuden. The applications presented here demonstrate the potential for using quantum chemical methods and molecular simulations to determine the mechanisms and rates of the thermal decomposition of polymers. The expectation is that these capabilities can be used to predict the flammability of materials and develop strategies to improve fire resistance. The thermal decompositions of poly(dihydroxybiphenylisophthalamide) and bisphenol C polycarbonate are investigated by performing density-functional calculations of potential energy surfaces of model compounds representing the polymers. Reactive molecular dynamics, a relatively new technique that extends conventional molecular dynamics to modeling chemical reactions, was used to simulate the thermal decomposition of polyisobutylene. The advantages and limitations of both computational approaches are discussed. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software is required in order to read it. Multireference Density Functional Approach to the Calculation of the Excited States of Uranium Ions This is the full text of a thesis written by Eric V. Beck which was presented to the Air Force Institute of Technology, Wright Patterson Air Force Base, Ohio in March 2007. An accurate and efficient hybrid Density Functional Theory (DFT) and Multireference Configuration Interaction (MRCI) model for computing electronic excitation energies in atoms and molecules was developed. The utility of a hybrid method becomes apparent when ground and excited states of large molecules, clusters of molecules, or even moderately sized molecules containing heavy element atoms are desired. In the case of large systems of lighter elements, the hybrid method brings to bear the numerical efficiency of the DFT method in computing the electron-electron dynamic correlation, while including non-dynamical electronic correlation via the Configuration Interaction (CI) calculation. Substantial reductions in the size of the CI expansion necessary to obtain accurate spectroscopic results are possible in the hybrid method. Where heavy element compounds are of interest, fully relativistic calculations based upon the Dirac Hamiltonian rapidly become computationally prohibitive, as the basis set requirements in four-component calculations increase by a factor of two or more in order to satisfy kinetic balance between the large electronic components and small positronic components, while the size of the MRCI Hamiltonian quadruples with respect to a non-relativistic calculation. In this hybrid method, applications to heavy element compounds such as bromine and uranium were accomplished through the use of relativistic elective core potentials, allowing for the first time both scalar relativistic and spin-orbit elect treatment necessary for the accurate calculation of electronic excitation energies in heavy elements in a Density Functional Theory Multireference Configuration Interaction Hybrid Model (DFT/MRCI) method. This implementation of the original hybrid method, developed by Grimme and Waletzke, was modified to remove inherent spin-multiplicity limitations, as well as reduce the number of free parameters used in the method from five to three. [Taken from abstract]. The thesis is available in PDF format so Adobe Acrobat software is required in order to read it. NASA Langley Research Center This is the home page of the NASA Langley Research Center. Its primary concerns are airframe systems, atmospheric sciences and structures and materials research. The site describes the research that the Center carries out, information on doing business with it, and provides access to LISAR, the Langley Image Scanning Archival and Retrieval system which contains a database of photographs of NASA and NACA research undertaken at Langley. The site also features the Langley Factsheet Server which provides full text details about many of Langley's research programmes, the Langley Technical Report Server (LTRS) for searching and browsing technical reports, some of which are available in full in PDF format, and latest news. NASA Tech Briefs Online : Engineering Solutions for Design and Manufacturing This newsletter site includes articles and news items on the latest spin-off developments from NASA including a TechSearch of over 6000 technologies available for license. Free subscription is available and an archive is available to search as well as a Tech Brief library to browse. A new NanoTech Brief is available as well as news items and articles on the latest developments in the bio-medical, materials, mechanics, motion control, manufacturing, machinery, photonics and test and measurement fields. Nonhalogen Fire-Resistant Plastics for Aircraft Interiors This provides access to a Federal Aviation Administration (FAA)written by Richard Lyon and dated January 2008. Strategies for developing fireproof aircraft cabin materials are reviewed in light of environmental legislation that restricts the use of halogens in plastics. The important physical and chemical processes of flaming combustion in terms of their effect on the heat release rate of a burning material are flame inhibition, fuel replacement, heat resistance, and intumescence. These fire resistance mechanisms, acting simultaneously or synergistically, are particularly effective at reducing heat release rate of a new generation of transparent plastics suitable for aircraft cabin interiors. [Taken from abstract]. The full text is available in PDF format so Adobe Acrobat software is required in order to read it. Office National d'Etudes et de Recherches Aerospatiales (ONERA) Office National d'Etudes et de Recherches A�rospatiales (ONERA) is the French national aerospace research establishment. It is a scientific and technical public establishment managed according to industrial and commercial practice, placed under the supervision of the Minister of Defense. Its missions are to develop and guide aerospace research; design, develop and implement the facilities it requires to conduct its research and testing; publish and promote the results of its research; and contribute to the education of engineers and scientists. In addition to an overview of current research projects and interests, facilities and expertise, the site does provide a searchable database of scientific publications. This includes articles published in journals, papers delivered before conferences, theses, Technical Notes (NT), other publications, but not unpublished research reports. Some recent documents are available in full text format. An French language version of the site is also available. Optical-Characterization and Modeling of Compositionally Matched Indium Arsenide-Antimonide Bulk and Multiple Quantum Well Semiconductors This is the full text of a thesis by Scott C. Phillips which was presented to the Air Force Institute of Technology (AFIT) in 2004. Indium arsenide-antimonide (InAs1-xSbx) semiconductors have been determined to emit in the 3-5m range, the window of interest for countermeasures against infrared electro-optical threats. This experiment set out to cross the bulk to quantum well characterization barrier by optically characterizing two sets of compositionally matched type I quantum well and bulk well material samples. Absorption measurements determined the bandgap energy of the bulk samples and the first allowed subband transition for the quantum wells. By collecting absorption spectra at different temperatures, the trend of the energy transitions was described by fitting a Varshni equation to them. The expected result of the quantum well always having slightly higher energy than its bulk counterpart was observed. An etalon effect was also observed in the quantum wells, caused by the cladding layers in those samples. Photoluminescence spectra were also collected to characterize the change in electron temperature (Te) as the excitation power was varied. As expected, Te increased with increasing power and increasing temperature. The start of the longitudinal optical phonon dominated cooling range due to excitation intensity was also determined for the samples from 1/Te. It was found that the quantum well required higher excitations intensities to achieve this effect. Lastly, the energy transitions found for the quantum well samples were compared to those found by a finite element method (femb) model. The predicted energies all laid a constant value above what was found experimentally, indicating the program had a translation error within it. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site. Outgassing Data for Selecting Spacecraft Materials Online This site features a database of outgassing data of materials intended for spacecraft use, obtained at the Goddard Space Flight Center (GSFC) Materials Engineering Branch, and utilising equipment developed at Stanford Research Institue (SRI) under contract to the Jet Propulsion Laboratory (JPL). The site provides a system description, and the possibility to download the entire Outgassing database. The Outgassing Materials Search function provides the capabilility to search all across materials tested at GSFC for determining the mass loss in a vacuum and for collecting the outgassed products. A Manufacturer Lookup allows to search on manufacturer name or code, or to browse the manufacturer list. There are also category and alphabetical listings and a report documentation page. Performance Materials Net This is a service that provides news and features about advanced and high-performance materials. Coverage includes advanced composites, engineering ceramics, performance plastics, and biomedical materials. All the items on the website are indexed so that information on specific applications, companies, or brands can be located using the menu links. The search engine can also be used to locate all relevant documents. Subscribers have free unlimited access, non-subscribers may view short descriptions of the content. There is a free email alert service and a forthcoming events area. Polymer Flammability This technical report (DOT/FAA/AR-05/14) was produced by the Fire Safety Branch of the Federal Aviation Administration (FAA) in May 2005 and was written by Richard E. Lyon and Marc L. Janssens. This report provides an overview of polymer flammability from a materials science perspective and describes currently accepted test methods to quantify burning behavior. Simplifying assumptions about the gas and condensed phase processes of flaming combustion provide mathematical relationships between polymer properties, chemical structure, flame resistance, and fire behavior that can be used to design fire-resistant plastics. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Polyurea Paint Marking Material Study This technical report (DOT/FAA/AR-TN06/46) was produced by the Federal Aviation Administration (FAA) in October 2006 and was written by Holly M. Cyrus and Renee Frierson. Pavement markings must endure the harsh airport environment. Standard waterborne, epoxy, methacrylate, and solvent base markings require frequent repainting causing the life-cycle cost to increase significantly. An elastomer material used on highways, called polyurea, has been identified as a potential alternative to existing standard pavement marking materials. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. PrePRINT Network : Department of Energy This service is a searchable gateway to preprint servers provided by the US Department of Energy (DOE) Office of Scientific and Technical Information (OSTI). It is possible to search one site, a group of sites, or all the sites, or to browse an alphabetical listing of all preprint sites included on the service. An additional feature notifies individuals of new preprints that match a personally defined profile of subject interests. Subject areas covered include physics, mathematics, computer science, nonlinear sciences, engineering, and materials science. Proceedings of the Institution of Mechanical Engineers, Part G : Journal of Aerospace Engineering Published six times a year, the Journal of Aerospace Engineering is a forum for the communication of ideas and methods presently in use at the forefront of technology in the field of aerospace engineering. It contains papers on both theoretical and practical aspects of all types of civil and military aircraft and spacecraft and their support systems. The scope is wide, covering research, design, development, production, operation, servicing and repair, components and auxiliary equipment, safety and reliability. The site provides contents information for the journal. If you wish to view full text check with your library to see if they have a subscription. Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials: Design and Applications Published four times a year, the Journal of Materials: Design and Application, is a forum for the communication of ideas and methods presently in use at the forefront of technology in the field of materials science. This journal is addressing a whole range of materials engineering and technology, which includes metallic materials, polymers, composites and ceramics. In addition, metal matrix composites and ceramic matrix composites are part of the portfolio. The site provides contents information for the journal. If you wish to view full text check with your library to see if they have a subscription. Proceedings of the Second International Conference on Alternative Aviation Fuels This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-98/73, compiled by Baylor University, dated March 1999. This report contains 50 technical presentations presented at the Second International Conference on Alternative Aviation Fuels. Baylor University, in Waco, Texas, hosted the conference on November 6-8, 1997. Topics covered in the papers and panel discussions included, Environmental impact of alternative aviation fuels; Cost-effectiveness and characteristics of alternative fuels; Alternative aviation fuel case studies, Fuel suppliers and manufactures responses to alternative fuels; and Barriers to commercialization. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library. Repair Types, Procedures – Part I
This is the full text publication that was assembled to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel (AVT) presented on 17-18 May 2010 in Prague, Czech Republic. Repair Types, Procedures – Part II
This is the full text publication that was assembled to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel (AVT) presented on 17-18 May 2010 in Prague, Czech Republic. Results of Intermediate-Scale Flammability Tests Performed on Hyperlon(tm) RB71 Aircraft Duct Insulation This provides access to a Federal Aviation Administration (FAA) report DOT/FAA AR-06/4 by Patricia Cahill, Tim Marker and John Reinhardt dated February 2006. Intermediate-scale flammability testing of Hypalon™ RB71, a thermal acoustical insulation primarily used to insulate ducts, was conducted in a section of a wide-body aircraft. The aircraft section was configured to represent the attic area of a transport category aircraft. Baseline tests were also conducted using metallized Tedlar™ film cover over fiberglass to wrap the ducts. Temperature versus time and the relative energy release rate versus time were evaluated and are presented in this report. [Taken from abstract]. The full text is available in PDF format from the online catalogue of the William J. Hughes Technical Center Library. Selected Current Aerospace Notices Provided by NASA, Selected Current Aerospace Notices (SCAN) is a weekly electronic current awareness journal that announces recently issued report and journal literature from the NASA scientific and technical information knowledge base. SCAN covers the full spectrum of aeronautics and aerospace-related information and segments it into subject groupings, or topics, which are narrower in scope than the 76 categories provided by Scientific and Technical Aerospace Reports (STAR). Furthermore, SCAN announces documents simultaneously in all relevant topics. Document citations announced in STAR are presented in only the one subject category deemed most appropriate. Each of the 186 SCAN topics is carefully tailored to fit the needs of a specialized research activity. New topics are added as the need arises, and others are retired or redefined as research demands dictate. The service is also searchable. Simulating the Distribution of Halon 1301 in an Aircraft Engine Nacelle With HFC-125 This provides access to a Federal Aviation Administration (FAA) technical note, DOT/FAA/AR-TN99/64, by Douglas Ingerson, dated August 1999. This technical note describes a procedure for utilizing an ozone-friendly simulant during fire suppression system development and certification testing. The full text of the report is available in PDF format from the online catalogue of the FAA William J. Hughes Technical Center Library. Stress Analysis of Silicon Carbide Microelectromechanical Systems using Raman Spectroscopy This is the full text of a thesis by Stanley J. Ness which was presented to the Air Force Institute of Technology (AFIT) in 2003. During the fabrication of Micro-Electro-Mechanical Systems (MEMS), residual stress is often induced in the thin films that are deposited to create these systems. These stresses can cause the device to fail due to buckling, curling, or fracture. Government and industry are looking for ways to characterize the stress during the deposition of thin films in order to reduce or eliminate device failure. Micro-Raman spectroscopy has been successfully used to analyze poly-silicon MEMS devices made with the Multi-User MEMS Process (MUMPS). Micro-Raman spectroscopy was selected because it is nondestructive, fast and has the potential for in situ stress monitoring. This research attempts to validate the use of Raman spectroscopy to analyze the stress in MEMS made of silicon carbide (SiC) using the Multi-User Silicon Carbide surface micromachining (MUSiCSM) process. Surface interferometry of fixed-fixed beam arrays and comb drive resonance test are employed to determine stress and compare it to the Raman values. Research also includes baseline spectra of 6H, 4H, and 15R poly-types of bulk SiC. Raman spectra of 1- to 2-m thick 3C-SiC thin films deposited on silicon, silicon nitride, and silicon oxide substrates are presented as an attempt to establish a baseline spectra for 3C-SiC, the poly-type of SiC found in MEMS made with the MUSiCSM process. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site. Subgrade CBR Values of Alpha Factor Determination Using Data Collected at the National Airport Pavement Test Facility This technical report (DOT/FAA/AR-TN07/14) was produced by the Federal Aviation Administration (FAA) in April 2007 and was written by Gordon F. Hayhoe. Full-scale traffic test results from tests run at the Federal Aviation Administration National Airport Pavement Test Facility (NAPTF) in 2000, 2001, and 2002 with four-wheel and six-wheel landing gears have previously been combined with results fromtests run by the U.S. Army Corps of Engineers in the early 1970s. The combined results were analyzed in a recent report, and updated alpha factor values were determined for four- and six-wheel gears at 10,000 coverages. The strength of the subgrades in the NAPTF test pavements was characterized by averages of CBR (California Bearing Ratio) measurements made at the surface of the subgrade before and after testing and CBR measurements made after testing at depths of one foot and two feet (30.48 cm and 60.96 cm) below the surface of the subgrade. A number of minor transcription and rounding errors were made in the original calculations of the average CBR values and, since publication of the previous report, results have become available from an additional trench opened in one of the test items. The average CBR values for the NAPTF tests are updated in this report, resulting in an increase in the computed four-wheel alpha factor of approximately 0.6 percent and a decrease in the computed six-wheel alpha factor of approximately 1.3 percent. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Survey of Nonglycol and Reduced Glycol Aircraft Deicing Methods : Final Report This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-99/18, by Jeremy Cornish and Frank Eyre, dated April 1999. This report presents the results of a survey of no glycol and low-glycol aircraft deicing practices, methods, and procedures used by the worlds airlines. The use of new, experimental techniques or reduced temperature buffer fluids are not within the scope of the study. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library. Synthesis and Characterization of Chlorinated Bisphenol-Based Polymers and Polycarbodiimides as Inherently Fire-Safe Polymers This provides access to Federal Aviation Administration (FAA) technical report DOT/FAA/AR-00/39, by Jennifer R. Stewart, August 2000. Two different types of polymers were synthesized and their degradation and combustion behavior were investigated. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library. Technical evaluation report on the AGARD Propulsion and Energetics Panel, 34th Meeting,8th colloquium on Reactions between Gases and Solids This is Research and Technology Organization (RTO) AGARD-AR-32, dated February 1971. The 34th Meeting of the Propulsion and Energetics Panel on Reactions between Gases and Solids was an interdisciplinary colloquium held at the Aerospace Research Laboratories of OAR at Wright-Patterson AFB, Dayton, Ohio, 13 - 16 October 1969. The program committee chairman was Colonel Paul G. Atkinson, Jr., USAF. The objective was to bring together experts in the diverse fields of corrosion, combustion, ablation, and erosion. Each of these fields is usually studied and practiced as a separate engineering specialty. Direct communication between specialists crossing interdisciplinary boundaries was intended to stimulate new insights in dealing with the many practical problems which involve some aspect of gas-solid reactions. The colloquium subject was selected by the Panel. The agenda was structured to cover the fundamentals of kinetics and surface phase reactions, with surveys of the individual fields, current advances in these fields by various NATO laboratories, and a roundtable discussion to consider the commonality of the various gas solid reactions. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (984.01KB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Test and Evaluation of the Halon 1301 and Nitrogen Inerting Against 23mm HEI Projectiles This technical report (AFFDL/TR/78-66) was produced by the Air Force Flight Dynamics Laboratory (AFFDL) in May 1978 and was written by Charles L. Anderson. This report presents the test results of an evaluation of Halon 1301 and nitrogen as fuel tank inertants. The inertants are compared to internal foam and are evaluated under near worse case conditions. The 23 cm HEI projectile is the primary threat investigated although the 23 cm API projectile and high velocity fragments were also tested. JP-4 fuel was used to obtain worst case fuel/oxygen mixtures. The report contains information on test setup, results, conclusions, and the fuel/oxygen ratio measurement and control technique. Significant data is included on the explosion overpressures versus inertant concentrations. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. The characterization and application of materials This is Research and Technology Organization (RTO) AGARD-LS-51, dated May 1971. This is a lecture series edited by the Structures and Materials Panel and the Consultant and Exchange Programme of AGARD. The Lecture Series will begin with a discussion of the systems approach to the selection and application of materials, to be given by Dr Robert Maddin. The second in the series will be given by Dr Walter S.Owen and will be primarily concerned with the characterization, selection and use of high strength steels. The third lecture will be given by Dr Joseph Pask and will be concerned with the characterization, selection and uses of ceramic materials. The fourth in the series will be given by Professor Wippler and will cover the characterization, selection and use of polymeric materials. Dr Kelly will present the fifth lecture which will deal with characterization, selection and use of composite materials. The last lecture will cover two fields of special interest to aerospace: aluminium alloys and titanium, their characterization and selection aspects. This lecture will be divided into two parts and will be presented by Mr Syre for the titanium, and by Mr Tigeot for the aluminium alloys part of the paper. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (25.52 MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. The Effectiveness of Ullage Nitrogen-Inerting Systems Against 30-mm High-Explosive Incendiary Projectiles This technical report (NWC/TP-7129) was produced by the Naval Weapons Center (NWC) in May 1991 and was written by J. Hardy Tyson and John F. Barnes. This report presents the data and results of tests conducted at the Naval Weapons Center to evaluate the use of nitrogen in aircraft fuel tanks to produce an inert atmosphere in the ullage. The objective of these tests was to define the limits of nitrogen effectiveness against explosive reactions in a large ullage space. Tests were conducted at simulated low, high and ambient altitudes. Testing included the evaluation of inert atmospheres containing 9, 12, 15, and 21% oxygen and the effects of these atmospheric conditions on reactions produced by a low-energy J-57 engine igniter and a comparatively high-energy 30-mm HEI projectile. All tests were conducted in a 30-cubic-foot steel simulator. A total of 65 tests were performed, including both control and inert tests. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. The Effects of Angular Orientation on Flame Spread Over Thin Materials This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-99/86, by J.G. Quintiere, dated December 1999. The report examines the flame spread characteristics of thin materials burning on an insulating substrate. A theoretical analysis is developed to predict the flame spread as a function of material properties, sample orientation, and flame spread direction. The full text of the report is available in PDF format from the online catalogue of the FAA William J. Hughes Technical Center Library. Thermal Analysis of Polymer Flammability This provides access to a Federal Aviation Administration (FAA) report DOT/FAA AR-07/2 by Richard E. Lyon ...[et al]dated Arpil 2007. A thermal analysis method is presented that uses controlled heating of polymer samples and complete combustion of the evolved gases to separately reproduce the condensed and gas phase processes of flaming combustion in a single laboratory test. Oxygen consumption calorimetry applied to the combustion gas stream gives the heat release rate history of the sample as a function of its temperature. The maximum rate of heat release and the temperature at which it occurs are polymer characteristics related to fire performance and flame resistance. [Taken from abstract]. The full text is available in PDF format from the online catalogue of the William J. Hughes Technical Center Library. Thermal Analysis of Polymer Flammability This technical report (DOT/FAA/AR-07/2) was produced by the Federal Aviation Administration (FAA) Office of Aviation Research and Development in April 2007 and was written by Richard E. Lyon, Robert Filipczak, Richard N. Walters, Sean Crowley and Stanislav I. Stoliarov. A thermal analysis method is presented that uses controlled heating of polymer samples and complete combustion of the evolved gases to separately reproduce the condensed and gas phase processes of flaming combustion in a single laboratory test. Oxygen consumption calorimetry applied to the combustion gas stream gives the heat release rate history of the sample as a function of its temperature. The maximum rate of heat release and the temperature at which it occurs are polymer characteristics related to fire performance and flame resistance. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it. Thermal Barrier Coatings This is Research and Technology Organization(RTO) AGARD Report, AGARD-R-823, dated April 1998. It was sponsored by the Advisory Group for Aerospace Research and Development. The report explains; Thermal barrier coatings are an emerging technology which will allow either increasing the inlet turbine temperatures or on the other hand decreasing the working temperature of the metal of the blades and consequently increasing their life-time. The Workshop allowed a survey of the state of the art, a description of the existing technologies or of the technologies under development, a review of the present knowledge of damage mechanisms, including microstructural, mechanical and thermal aspects, and an account of the advantages and drawbacks of the various families as perceived by engine manufacturers and users. A final discussion was held to identify the needs for further R & D. Bibliographic details and an abstract are available in HTML format and the full text is available in PDF format (0.3 Mb)from the RTO's web site. Thermal Decomposition Mechanism of 2,2-Bis-(4-Hydroxyphenyl)-1,1-Dichloroethylene-Based Polymers : Final Report This provides access to a Federal Aviation Administration (FAA) report, DOT/FAA/AR-00/42, by Michael L. Ramirez, dated February 2001. The report describes a study to establish the decomposition mechanism of two thermoplastics and one thermoset BPC-based polymer. This work forms part of the FAA's efforts to develop fire-resistant materials for commercial aircraft cabins. The full text of the report is available in PDF format, from the online catalogue of the FAA William J. Hughes Technical Center Library. Thermo-Kinetic Model of Burning This provides access to a Federal Aviation Administration (FAA) technical report DOT/FAA/AR-TN08/17 written by Stanislav Stoliarov and Richard Lyon dated May 2008. One main obstacle in developing more effective passive fire protection for transportation is the lack of a quantitative understanding of the relations between the results of various materials fire tests used in this field. The need for multiple testing techniques arises from the complexity of fire phenomena and their sensitivity to environmental conditions. This study addressed this problem by developing a computational tool that predicts the behavior of materials exposed to fire. While it is not expected that this tool will eliminate the need for fire testing, the goal is to considerably reduce the number and complexity of the tests necessary for a comprehensive characterization of the materials of interest. The foundation of this tool is a mathematical model that describes transient thermal energy transport, chemical reactions, and the transport of gases through the condensed phase. The model also captures important aspects of a material’s behavior such as charring and intumescence. This technical note provides a detailed description of the one-dimensional version of this model and summarizes the results of the model’s verification. [aken from abstract]. The full text is available in PDF format so Adobe Acrobat software is required in order to read it. Thermophysical properties of solid materials - Cooperative thermal expansion measurements up to 1000 C. Project section 1A This is Research and Technology Organization (RTO) AGARD-AR-31, dated March 1971. As a part of a major project concerning thermophysical properties of solid materials at high temperatures this is a report on the special section of this project dealing with thermal expansion up to temperatures of 1000°C. The complete project TX 44 is aimed at determining absolute accuracy of thermophysical property data of engineering materials at high temperatures by means of a cooperative measurement programme. The results are to indicate the best way of obtaining accurate data. This involves clarifying the following: (1) whether it is best to experimentally determine the properties of a material at the temperatures for which the data are needed, (2) whether known low temperature values on the material considered should be extrapolated to high temperatures, (3) whether it is better to derive estimated high temperature data of the material considered by a comparison with a similar material whose data are available from data compilations. Additionally the aim of the Project Section "Thermal Expansion up to 1OOO"C" is to determine the thermal expansion of solid materials up to 1000°C, which is considered conventionally as the most simple measurement within the realm of thermophysical property measurements. Customarily such measurements, especially in industrial laboratories, are performed by means of pushrod dilatometers, using both quartz glass and alumina reference systems. In as much as this type of apparatus does not yield absolute values and the accuracy of data obtained thereby is frequently considered in doubt, it is a special objective of this project section to determine the accuracy of this type of measurements by using the noble metals gold and platinum. A further objective is to investigate the thermal expansion behaviour of technical materials up to 1OOO"C, to find out if such materials can be used as calibration standards and to establish if an extension of the study on these materials to higher temperatures is justified. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (6.02MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library. Using Timeresolved Photoluminescence to Measure the Excitation and Temperature Dependence of Carrier Relaxation in Midwave Infrared Semiconductors This is the full text of a thesis by Kevin Cumblidge which was presented to the Air Force Institute of Technology (AFIT) in 2004. Research in the field of midwave infrared (MWIR) semiconductor photonic devices has led to applications in a variety of disciplines including atmospheric monitoring, optical communications, noninvasive glucose testing for diabetics, and infrared (IR) countermeasures. One of the limiting factors for improving the modulation rates of MWIR devices is the carrier relaxation time. This is the time required for energetic carriers to cool to the edge of their respective bands in a bulk semiconductor material, or to the bottom of a well through interand intrasubband scattering in a quantum well (QW) structure. From these lower energy states, they can then recombine radiatively in photonic devices. This investigation utilized the nonlinear optical technique of frequency upconversion to perform timeresolved luminescence spectroscopy on epitaxial bulk InAs, InAsSb/InAlAsSb type I QW structure, and InAs/GaInSb type II QW samples to calculate carrier relaxation times in each as a function of excitation irradiance and sample temperature. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site. Wright Air Development Center Digital Collection Wright-Patterson Air Force Base has been a major centre of aeronautical and aeorspace design and development for many years. The purpose of this site is to document various aspects of the Wright Air Development Center (WADC) period in this long history. The site, which is hosted by the Galvin Library at Illinois Institue of Technology, provides access to a range of information resources. The history section includes a timeline of important events; image gallery, an overview of WADC's association with Illinois Institute of Technology; and features on the Center's involvement in both the "space race" and the Roswell incident. The reference shelf contains a linked bibliography of historical sources relating to the Wright Air Development Center. Some of these publications, such as, Birthplace, Home and Future of Aerospace... The Evolution of Aeronautical Development at the Aeronautical Systems Center, are available in full text (pdf format). The Digital Collection provides access to WADC technical report information. The collection can be browsed by report number, date, author or corporate author. Many of the reports are available in full text. A full bibliography of reports is also available in pdf, MS Excel, or interactive (requires Internet Explorer v. 4.01 and Microsoft Office Web Components) formats. |
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