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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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At least 343 records · Page 19
All sourcesNASA NTRSDOE OSTI
NASA NTRS1976

Mass spectrometry of aerospace materials

Mass spectrometry is used for chemical analysis of aerospace materials and contaminants. Years of analytical aerospace experience have resulted in the development of specialized techniques of sampling and analysis which are required in order to optimize results. This work has resulted in the evolution of a hybrid method of indexing mass spectra which include both the largest peaks and the structurally significant peaks in a concise format. With this system, a library of mass spectra of aerospace materials was assembled, including the materials responsible for 80 to 90 percent of the contamination problems at Goddard Space Flight Center during the past several years.

Colony, J. A.↗
NASA NTRS1976

Entry into outer planet environments. II - Performance of volume reflecting hyperpure silica heat shields

The performance of hyperpure silica heat shields that backscatter incident radiation in the depths of the material, i.e., a volume reflecting heat shield, is mapped for probes entering the atmospheres of Saturn and Uranus. Three models of each atmosphere are considered; the warm, nominal, and cool models. The most recent thermophysical and optical properties of hyperpure silica are employed. Detailed incident radiative spectra and the effects of ablation on radiative and convective heating obtained from benchmark flowfield solutions are used. In-depth material response is examined and results are presented in terms of the peak rear-face temperature as a function of initial thickness for each atmosphere. Results are compared with carbon phenolic heat-shield requirements.

Howe, J. T.↗
NASA NTRS1976

Environmental charging tests of spacecraft thermal control louvers

The environmental charging of spacecraft surfaces program consists, in part, of experimental evaluation of material response to the environmental charged particle flux. A flight type spacecraft thermal control louver assembly has been tested in an electron flux. The louver blade surface potential, the louver assembly currents, and the relatively high number of discharges observed in the electron environment are self-consistent results. The unexpected result of this testing was the flutter observed when the louvers were closed. The flutter is about 1 to 2 Hz in frequency and is probably electrostatically induced.

Berkopec, F. D.↗
NASA NTRS1977

Engineering approximations for Jovian entry

A code has been written to describe the behavior of an ablating heat shield throughout the entire maneuver into a planetary atmosphere. The code includes a trajectory computation for a variable mass, a computation of the heating history and distribution over the probe, ablation effects, indepth material response, and shape change. The code draws the initial and final shapes of the heat shield and computes its initial and final mass. Results are compared with those of other investigators, and solutions are obtained for a silica heat shield entering three model atmospheres of Jupiter. The effects of varying half cone angle and entry angle are examined as well as shape change effects. The so-called 'cusping effect' in the stagnation region is examined.

Lasher, L. E.↗
NASA NTRS1977

Observations and interpretation of the infrared spectrum of HD 44179

Infrared spectra of HD 44179 have been obtained for the 3040-, 1150-, and 890-kayser emission features. The strengths of the features put constraints on the possible constituents of the materials responsible for each emission feature. The 3040-kayser feature can be due to emission either from a solid (if it arises from a different region than the 890-kayser feature) or from a gas-phase molecule. The 8-13-micron spectrum is fitted with a simple model employing carbonates plus a dielectric in emission and silicates in absorption. It is suggested that amorphous carbon is the dielectric responsible for the featureless underlying continuum.

Bregman, J. D.↗
NASA NTRS1978

The STAGS computer code

Basic information about the computer code STAGS (Structural Analysis of General Shells) is presented to describe to potential users the scope of the code and the solution procedures that are incorporated. Primarily, STAGS is intended for analysis of shell structures, although it has been extended to more complex shell configurations through the inclusion of springs and beam elements. The formulation is based on a variational approach in combination with local two dimensional power series representations of the displacement components. The computer code includes options for analysis of linear or nonlinear static stress, stability, vibrations, and transient response. Material as well as geometric nonlinearities are included. A few examples of applications of the code are presented for further illustration of its scope.

Almroth, B. O.↗
NASA NTRS1979

Numerical simulation of experiments in the Giant Planet Facility

Utilizing a series of existing computer codes, ablation experiments in the Giant Planet Facility are numerically simulated. Of primary importance is the simulation of the low Mach number shock layer that envelops the test model. The RASLE shock-layer code, used in the Jupiter entry probe heat-shield design, is adapted to the experimental conditions. RASLE predictions for radiative and convective heat fluxes are in good agreement with calorimeter measurements. In simulating carbonaceous ablation experiments, the RASLE code is coupled directly with the CMA material response code. For the graphite models, predicted and measured recessions agree very well. Predicted recession for the carbon phenolic models is 50% higher than that measured. This is the first time codes used for the Jupiter probe design have been compared with experiments.

Green, M. J.↗
NASA NTRS1979

Lunar libration region L4 photometry

Photometry of the lunar libration region L4 obtained in double umbra during the lunar orbital flight of Apollo 15 is reported. A four-minute photographic exposure of the region centered at celestial coordinates 23 h 14 m, -1.8 deg was made using a 35-mm camera at f/1.2 in the command module pilot's window. The film had been calibrated to the sun's surface brightness, and scene brightness information was converted to digital form, followed by high-speed digital processing with vignetting removal to obtain absolute photometric values. Results reveal an elliptical brightness region 16 x 12 deg in extent with an absolute brightness of 3.3 x 10 to the -14th sun surface brightness units. The mass of the scattering material responsible for the effect is estimated to be between 6 x 10 to the 18th and 2 x 10 to the 7th g.

Mercer, R. D.↗
NASA NTRS1979

Path dependence of J in three numerical examples

Three cracked geometries are studied with the aid of a new finite element model. The procedure employs a variable singularity at the crack tip that tracks changes in the material response during the loading process. Two of the problems are tension-loaded center-crack panels and the other is a three-point bend specimen. Results usually agree with other numerical and analytical analyses, except the finding that J is path dependent as a substantial plastic zone develops. Credible J values are obtained near the crack tip and J shows a significant increase as the radius of J path increases over two orders of magnitude. Incremental and deformation theories are identical provided the stresses exhibit proportionality found in the far field stresses but not near the tip.

Karabin, M. E., Jr.↗
NASA NTRS1981

Empirical relationship of ultraviolet extinction and the interstellar diffuse bands

New ultraviolet colors are presented for 110 hot stars. These data are combined with infrared colors and diffuse-band measurements to study the relationship of diffuse interstellar bands (4430, 5780, 6284 A) to the overall extinction curve. Equivalent widths of 5780 A and 6284 A are not well correlated with infrared, visible, or ultraviolet extinction measurements for stars in this sample. The central depth of 4430 A is well correlated with visible and infrared extinction, but less well correlated with UV extinction at 1800 A. The wavelength 4430 A is strongly correlated with the strength of the 2200-A bump. The data suggest that if small grains account for the general rise in UV extinction, the diffuse bands are not formed in these grains. The wavelength 4430 A may well arise in large grains and/or in the material responsible for the 2200-A bump. Correlations with UV extinctions derived by other authors are discussed in detail. It is suggested that definitions of extinction parameters and band shapes, as well as selection effects in small samples of stars, may still compromise conclusions based on correlation studies such as are being attempted.

Wu, C.-C.↗
NASA NTRS1981

Dissipation due to obliquity-induced tides in a Kelvin-Voigt viscoelastic body

A calculation is conducted regarding the local and total dissipation rate of mechanical energy for an incompressible, Kelvin-Voigt body in a circular orbit with finite obliquity. The considered material is characterized by a shear modulus and a viscosity. Of the two parameters, only the shear modulus is known. An investigation is conducted regarding the variation of the total dissipation rate with viscosity. For small values of the viscosity the Kelvin-Voigt material approximates the behavior of an elastic solid. In this range, results for the earth-moon system are similar to those obtained by Peale and Cassen (1978) using a modified form of the elastic solution. For large values of the viscosity the results are qualitatively different from those in the 'elastic' range, as viscous effects dominate the material response.

Vanarsdale, W. E.↗
NASA NTRS1982

The mechanics of fatigue in composite laminates

A status report is presented for the development of the mechanics of fatigue in composite materials. A concensus is noted on the need to construct mechanics treatments on the basis of precisely defined damage states which are both characteristic of the material and independent of as many extensive variables, such as load history, as possible. This approach is in keeping with the use of a single crack as the characteristic damage state in homogeneous materials, which has provided a well defined and precise boundary value problem that can be used in the description and prediction of damaged material response. The utility of stress redistribution concepts in determining residual strength, stiffness, and life in composite laminates is also recognized.

Reifsnider, K. L.↗
NASA NTRS1982

Refurbishment of SRB aluminum components by walnut hull blast removal of protective coatings

A test program was conducted to develop, optimize, and scale up an abrasive blasting procedure was developed for refurbishment of specific SRB components: aft skirt, forward skirt, frustrum, and painted piece parts. Test specimens utilizing 2219 T87 aluminum substrate of varying thicknesses were prepared and blasted at progressively increasing pressures with selected abrasives. Specimens were analyzed for material response. The optimum blasting parameters were determined on panel specimens and verified on a large cylindrical integrated test bed.

Colberg, W. R.↗
NASA NTRS1983

Multiaxial Cyclic Thermoplasticity Analysis with Besseling's Subvolume Method

A modification was formulated to Besseling's Subvolume Method to allow it to use multilinear stress-strain curves which are temperature dependent to perform cyclic thermoplasticity analyses. This method automotically reproduces certain aspects of real material behavior important in the analysis of Aircraft Gas Turbine Engine (AGTE) components. These include the Bauschinger effect, cross-hardening, and memory. This constitutive equation was implemented in a finite element computer program called CYANIDE. Subsequently, classical time dependent plasticity (creep) was added to the program. Since its inception, this program was assessed against laboratory and component testing and engine experience. The ability of this program to simulate AGTE material response characteristics was verified by this experience and its utility in providing data for life analyses was demonstrated. In this area of life analysis, the multiaxial thermoplasticity capabilities of the method have proved a match for the actual AGTE life experience.

Mcknight, R. L.↗
NASA NTRS1984

Three-dimensional Stress Analysis Using the Boundary Element Method

The boundary element method is to be extended (as part of the NASA Inelastic Analysis Methods program) to the three-dimensional stress analysis of gas turbine engine hot section components. The analytical basis of the method (as developed in elasticity) is outlined, its numerical implementation is summarized, and the approaches to be followed in extending the method to include inelastic material response indicated.

Wilson, R. B.↗
NASA NTRS1984

Aerothermodynamic environment and thermal protection for a Titan aerocapture vehicle

This paper presents thermal protection system (TPS) requirements for a potential Titan aerocapture vehicle. Shock-layer solutions are obtained for a nominal trajectory through the current Titan model atmosphere. Fully laminar and fully turbulent solutions are presented along the blunted fore-cone in the windward symmetry plane of a bent-biconic vehicle. Using these solutions to define the aerothermodynamic environment, transient material-response solutions are obtained for a Galileo-type TPS with a carbon-phenolic ablator heat shield. Shock-layer results indicate that turbulent flow is the more realistic flow condition. They also show that the lengthy aerocapture heating pulse is dominated by convective heating. The TPS results show that the required insulation thickness is uniformly about 4 cm along the fore-cone because of the long heat-soak period. The total heat-shield thickness is 6.4 cm at the stagnation point, and 4.7 cm near the end of the fore-cone. These TPS requirements are greater than those presented in a previous Titan aerocapture study.

Green, M. J.↗
NASA NTRS1984

Infrared photometry of Comet Bowell and other comets

Broad-band and intermediate-band infrared photometry of Comets Bowell, Elias, and Gunn is presented. The data for Comet Bowell show that the strongly depressed albedo near 3 microns observed by Campins and colleagues (1982) is very broad and extends at least to 4 microns. Scattering calculations indicate that existing infrared data do not provide direct, observational evidence for the presence of H2O ice. However, the material responsible for the 3-micron absorption observed by Campins and colleagues remains therefore unidentified.

Dwek, E.↗