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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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The polarizer is briefly described. The polarization of the whole pulse is not significantly different from zero (-0.15 plus or minus 0.70 per cent). Polarization measurements of the leading edge and trailing edge of the main pulse are also given.
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The infinitely long cylindrical shell under axial compression with axisymmetric sinusoidal imperfections is considered. The bifurcation problem is formulated exactly, and a complete family of buckling modes is identified. Koiter's (1963) upper bound pertains to the critical stress associated with one restricted set of modes, and the critical stress for a set of long wavelength modes reproduces some numerical results obtained by Almroth (1966). The initial postbuckling analysis is also formulated exactly. An exact analytical solution is obtained for the limiting case of modes with infinitely long wavelengths, and numerical analysis is used to solve the equations for the other cases. An appendix gives the details of the analysis.
This paper summarizes and evaluates the work done on the elastic analysis of the surface flaw problem by the application of the alternating method. An attempt is made to describe the alternating method and to present the history of its application to the surface flaw problem and to related problems in fracture mechanics. Stress intensity factors obtained by this method are summarized and compared. Results are also compared to those obtained by investigators using other methods of analysis. An evaluation of the use of the alternating method is presented with the purpose of pointing out the advantages and disadvantages in the application of this technique to the surface flaw problem.
Potentially automated pultrusion technique has been provided for production of curved, glass-reinforced polyimide, epoxy, and graphite reinforced structures. Specially designed apparatus has been manufactured for production of curved structures.
Utilize coaxial horn feed to illuminate reflector; feed has inner horn for X-band, and outer horn for S-band. Tracking error signals for servo correction are derived from measurements of relative phase and relative amplitude between two modes.
The fabrication of full-size structural rings from composite materials is described. Results of glass/epoxy and graphite/epoxy hat stringer sections prepared by pultrusion are discussed.
An experimental study was made of the local and average heat-transfer characteristics of a single turbulent air jet impinging on the concave surface of a hemisphere. Correlations were developed for expressing the effects of a number of dimensionless variables on the local and average Nusselt numbers. Results of the present study are compared with those from a similar study concerning a concave surface of a semicylindrical shell.
Many similarities between Martian and lunar multi-ringed basins are outlined. There is a similar relation between basin size and number of rings; the second ring seems to appear in the crater-basin continuum in roughly the same diameter range. The similarities are tentatively considered great enough to indicate that Martian and lunar basins were formed by the same process. Morphological and statistical studies of lunar basins have strongly indicated this process to be impact.
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A technique developed by Regge and Wheeler (1957) is applied in the Schwarzschild background geometry to treat the radiation emitted by a test particle moving at a speed close to the local speed of light in the vicinity of a black hole. An analytic expression is obtained for the gravitational and electromagnetic radiation spectrum of a particle traveling in a highly relativistic orbit around a Schwarzschild blac hole.
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Antenna includes two sets of linearly polarized elements. Each set contains slots in parallel array. Sets are mutually orthogonal and are driven in phase quadrature. By changing lengths of slots or their separations, antenna beamwidth can be changed over wide range. Similar results are achieved with dipole configuration.
Numerical methods and computer programs for studying the stability and evolution of orbits of large eccentricity are presented. Methods for determining launch windows and target dates are developed. Mathematical models are prepared to analyze the characteristics of specific missions.