Aeronautics

The three sets of data chosen for the comparisons between experiment and simulation have been supplied by Dr. S. K. Burke of the DSTO Aeronautical and Maritime Research Laboratory (Melbourne, Australia). 

Besides the material based characteristics, the difference of density of the used particle/substrate combination is a very important criterion. The difference of density influences the contrast of the radiographic tests. Tungsten carbides were used as mechanically resistant particles and titanium based alloys as substrate. The substrate material is marked by an advantageous relation of strength to density. This material is often used in aeronautics, astronautics, and for modification of boundary layers. The density of tungsten carbide (15.7 g/cm ) is about 3.5 times higher than the density of titanium (4.45-4.6 g/cm ). 

Products, processes, organization Sustainable mobility and intermodality New perspectives in aeronautics Marine technologies... 

It turns out that there is another branch of mathematics, closely related to tire calculus of variations, although historically the two fields grew up somewhat separately, known as optimal control theory (OCT). Although the boundary between these two fields is somewhat blurred, in practice one may view optimal control theory as the application of the calculus of variations to problems with differential equation constraints. OCT is used in chemical, electrical, and aeronautical engineering where the differential equation constraints may be chemical kinetic equations, electrical circuit equations, the Navier-Stokes equations for air flow, or Newton s equations. In our case, the differential equation constraint is the TDSE in the presence of the control, which is the electric field interacting with the dipole (pemianent or transition dipole moment) of the molecule [53, 54, 55 and 56]. From the point of view of control theory, this application presents many new features relative to conventional applications perhaps most interesting mathematically is the admission of a complex state variable and a complex control conceptually, the application of control teclmiques to steer the microscopic equations of motion is both a novel and potentially very important new direction. 

Kaye, A., 1962. Non-Newtonian Flow in Incompressible Fluids, CoA Note No, 134, College of Aeronautics, Cranfleld. 

K. M. Kratsch, J. C. Schutzler, and D. A. Pitman, Carbon—Carbon 3D Orthogonal Material Behavior Ad AA Paper No. IThA, AlA A-ASME-S AE 13th Stmctural Dynamics and Materials Conference, 1972), American Institute of Aeronautics and Astronautics, New York, 1972. 

N. Kubota, "Survey of Rocket PropeUants and Their Combustion Characteristics," in K. K. Kuo and M. Summerfield, eds.. Fundamentals of Solid Propellant Combustion, Vol. 90, Progress in Astronautics and Aeronautics, AJAA, 1984. 

Monographs on rockets and rocket propellants by the National Aeronautics and Space Administration (NASA), Lewis Research Center, Cleveland. These iaclude the foUowiag Solid Propellant Selection and Characteri tion, Report SP-8064,1971 Solid Rocket Motor Peformance, Report SP-8039,1971 Solid Rocket Motor Igniters, Report SP-8051,1971 Solid Rocket Motor Metal Cases, Report SP-8025, 1970, and Captive Eire Testing of Solid Rocket Motors, Report SP-8041,1971. 

The Ohio State University (OSU) calorimeter (12) differs from the Cone calorimeter ia that it is a tme adiabatic instmment which measures heat released dufing burning of polymers by measurement of the temperature of the exhaust gases. This test has been adopted by the Federal Aeronautics Administration (FAA) to test total and peak heat release of materials used ia the iateriors of commercial aircraft. The other principal heat release test ia use is the Factory Mutual flammabiHty apparatus (13,14). Unlike the Cone or OSU calorimeters this test allows the measurement of flame spread as weU as heat release and smoke. A unique feature is that it uses oxygen concentrations higher than ambient to simulate back radiation from the flames of a large-scale fire. 

In April of 1991, the U.S. National Aeronautics and Space Administration concluded that o2one depletion was occurring even faster than had been estimated, and at the third meeting of the patties to the Montreal Protocol in June of 1991, an eadiet phaseout of controlled substances was proposed. An assessment of the technical and economic consequences of a 1997 phaseout is cuttendy underway, and further acceleration of the phaseout schedule to as soon as 1995 seems likely. Many countnes already have undatetaHy banned or curbed the use of controlled substances well ahead of the Montreal Protocol timetable. As of eadyjuly 1992, there were 81 parties to the Protocol. 

Testing and Standards. Requirements for extmsion and mol ding grades are cited in ASTM specifications (79) and in Federal specification LP-389A of May 1964 (80). For fabricated shapes, FEP film and sheet are covered by Aeronautical Material Specifications (AMS) 3647 and LP-523 (81). Besides the specifications covered by the Fluorocarbons Division of the Society of the Plastics Industry, Inc. (82), other specifications are Hsted in Reference 83. 

The principal uses of PCTFE plastics remain in the areas of aeronautical and space, electrical/electronics, cryogenic, chemical, and medical instmmentation industries. AppHcations include chemically resistant electrical insulation and components cryogenic seals, gaskets, valve seats (56,57) and liners instmment parts for medical and chemical equipment (58), and medical packaging fiber optic appHcations (see Fiber optics) seals for the petrochemical /oil industry and electrodes, sample containers, and column packing in analytical chemistry and equipment (59). 

In addition to carbon and glass fibers ia composites, aramid and polyimide fibers are also used ia conjunction with epoxy resias. Safety requirements by the U.S. Federal Aeronautics Administration (FAA) have led to the development of flame- and heat-resistant seals and stmctural components ia civiUan aircraft cabias. Wool blend fabrics containing aramids, poly(phenylene sulfide), EDF, and other inherently flame-resistant fibers and fabrics containing only these highly heat- and flame-resistant fibers are the types most frequently used ia these appHcations. 

Hydrogen Safety Manual, Report TM-X-52454, National Aeronautics and Space Administration, Washkigton, D.C., 1968. 

B. Rosen, V. H. Dayan, and R. L. Proffit, Hydrogen Teak and Fire Detection A. Survey, Rep. SP-5092, National Aeronautics and Space Administration, Washkigton, D.C., 1979. 

S. Gordon and B. McBride, Computer Program for Calculation of Complex Chemical Equilibrium Compositions, NASA SP-273, N ational Aeronautics and Space Administration, Washington, D.C., 1971. 

Color Color Association of the United States 24 East 39th Street New York, NY 10016 Color standards for fabrics, paints, wallpaper, plastics, floor coverings, automotive and aeronautical materials, china, chemicals, dyestuffs, cosmetics, etc. 

Laminated and Reinforced Metals" in ECT3rd ed., Vol. 13, pp. 941—967, by C. C. Chamis, National Aeronautics and Space Administration. 

A smaller factor in ozone depletion is the rising levels of N2O in the atmosphere from combustion and the use of nitrogen-rich fertilizers, since they ate the sources of NO in the stratosphere that can destroy ozone catalyticaHy. Another concern in the depletion of ozone layer, under study by the National Aeronautics and Space Administration (NASA), is a proposed fleet of supersonic aircraft that can inject additional nitrogen oxides, as weU as sulfur dioxide and moisture, into the stratosphere via their exhaust gases (155). Although sulfate aerosols can suppress the amount of nitrogen oxides in the stratosphere... 

S. E. Harrison and co-workers, NASA Accession No. N65-24791, Rep. No. AD 461315, National Aeronautics and Space Administration,... 

Selenium and selenium compounds are also used in electroless nickel-plating baths, delayed-action blasting caps, lithium batteries, xeroradiography, cyanine- and noncyanine-type dyes, thin-film field effect transistors (FET), thin-film lasers, and fire-resistant functional fluids in aeronautics (see... 

C. F. Key, J. G. Austin, and J. W. Bransford, Flammability of Materials in Gaseous Ouygen Environments, NASA TMX-64783, National Aeronautics and Space Administration, Washiagton, D.C., Sept. 1973. 

H. J. Halberstadt, Proceedings of the 8th Intersociety Energy Conversion and Engineering Conference, American Institution of Aeronautics and Astronautics, New York, 1973, pp. 63—66. 

JSiational Conference of Spacecraft Sterili tion California Institute of Technology, U.S. National Aeronautics and Space Administration Technical Information Division, Calif., 1966. 

Engineering Sciences Data E nit. Approximate Data on the Viscosity of Some Common Eiquids, Item No. 66024, Royal Aeronautical Society, London, July 1966. 

R. H. Edwards, Eow Density Flows through Tubes andNoyyles, Vol. 51, Pt. 1, American Institute of Aeronautics and Astronomy, New York, 1977. 

H. F. Butze and R. C. Ehlers, Effect of Fuel Properties on Peformance of a Single Aircraft Turbojet Combustor, NASA TM X-71789, National Aeronautics and Space Administration, Lewis Research Center, Cleveland, Ohio, Oct. 1975. 

Since World War 11, the U.S. space program and the military have used small amounts of insoluble chromates, largely barium and calcium chromates, as activators and depolarizers in fused-salt batteries (214,244). The National Aeronautics and Space Administration (NASA) has also used chromium (111) chloride as an electrolyte for redox energy storage cells (245). 

J. W. McBain and co-workers. Foaming of Aircraft-Fngine Oils as a Problem in Colloid Chemist NACA ARR No. 4105, National Advisory Committee for Aeronautics, Stanford, Calif., 1944. 

Extracted from U.S. Standard Atmosphere, 1976, National Oceanic and Atmospheric Administration, National Aeronautics and Space Administration and tte U.S. Air Force, Washington, 1976. Z = geometric altitude, T = temperature, P = pressure, g = acceleration of gravity, M = molecular weight, a = velocity of sound, i = viscosity, k = thermal conductivity, X = mean free path, p = density, and H = geopotential altitude. The notation 1.79.—5 signifies 1.79 X 10 . ... 

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