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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 1,621 records · Page 90
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Remote measurement of chlorophyll concentration and secchi-depth using the principal components of the ocean's color spectrum

Statistical results and conclusions are presented, based on direct comparisons of the ocean's color and chlorophyll concentration. The ocean color and ground truth data for this analysis were collected during Mission 140 of NASA's NP3A earth resources aircraft over the period from 6 through 14 August 1970. During this experiment, chlorophyll and light attenuation data were collected. All sets of comparative observations are simultaneous in the sense that the ship began sampling when the aircraft came overhead.

Mueller, J. L.↗
NASA NTRS1972

Investigation of the use of microwave image line integrated circuits for use in radiometers and other microwave devices in X-band and above

Program results are described in which the use of a/high permittivity rectangular dielectric image waveguide has been investigated for use in microwave and millimeter wavelength circuits. Launchers from rectangular metal waveguide to image waveguide are described. Theoretical and experimental evaluations of the radiation from curved image waveguides are given. Measurements of attenuation due to conductor and dielectric losses, adhesives, and gaps between the dielectric waveguide and the image plane are included. Various passive components are described and evaluations given. Investigations of various techniques for fabrication of image waveguide circuits using ceramic waveguides are also presented. Program results support the evaluation of the image line approach as an advantageous method for realizing low loss integrated electronic circuits for X-band and above.

Knox, R. M.↗
NASA NTRS1970

Multipath errors in range rate measurement by a TDRS/VHF - GRARR

Range rate errors due to multipath reflection are calculated for a tracking and data relay satellite system using the VHF Goddard range and range rate (GRARR) system. At VHF the reflection is primarily specular, and the strength of the multipath relative to the direct path can be modeled in terms of the geometry and the surface characteristics, specifically the root-mean-square (rms) ocean wave height. The uplink and downlink multipath introduces phase jitter on the GRARR carrier and subcarrier. The derivation of these effects is reviewed leading to an expression for the rms range rate error. The derivation assumed the worst-case orbital configurations in which there was very little relative specular Doppler. This means that the specular multipath interference was not attenuated by the carrier and subcarrier PLL transfer functions. Curves of range rate error are presented as a function of grazing angle with wave height 0.3 to 0.7 meters and spacecraft altitude 100 to 700 miles as parameters.

Sohn, S. J.↗
NASA NTRS1972

Propagation of radio waves through the lower atmosphere of Venus

A simplified model of the Venus atmosphere is developed providing the loss factor profile of the atmosphere. With this profile the atmospheric attenuation as it depends upon the incidence angle is calculated for wavelengths between 2 cm and 20 cm. It is shown that the signal-to-noise ratios for a real aperture radar, a synthetic aperture radar, and communication links between a satellite and a landing probe achieve maximum values by the proper choice of the wavelengths. Furthermore, it turns out that the wavelength dependence is less crucial for the synthetic aperture radar compared to the other cases.

Richter, K. R.↗
NASA NTRS1972

Estimation of sea surface temperature from remote measurements in the 11-13 micron window region

The Nimbus-4 IRIS data was examined in the spectral region 775 to 1250/cm (8-13 microns) for useful information to determine the sea surface temperature. The high spectral resolution data of IRIS was degraded to low resolution by averaging to simulate a multi-channel radiometer in the window region. These simulated data show that within the region 775-975/cm (12.9-10.25 microns) the brightness temperatures are linearly related to the absorption parameters. Such a linear relationship is observed over cloudy as well as clear regions and over a wide range of latitudes. From this linear relationship it is feasible to correct for the atmospheric attenuation and get the sea surface temperature, accurate to within 1 K, in a cloud free field of view. The information about the cloud cover is taken from the TV pictures and BUV albedo measurements on board the Nimbus-4 satellite.

Prabhakara, C.↗
NASA NTRS1972

Full scale subsonic wind tunnel requirements and design studies

The justification and requirements are summarized for a large subsonic wind tunnel capable of testing full-scale aircraft, rotor systems, and advanced V/STOL aircraft propulsion systems. The design considerations and constraints for such a facility are reviewed, and the trades between facility test capability and costs are discussed. The design studies showed that the structural cost of this facility is the most important cost factor. For this reason (and other considerations such as requirements for engine exhaust gas purging) an open-return wind tunnel having two test sections was selected. The major technical problem in the design of an open-return wind tunnel is maintaining good test section flow quality in the presence of external winds. This problem has been studied extensively, and inlet and exhaust systems which provide satisfactory attenuation of the effects of external winds on test section flow quality were developed.

Kelly, M. W.↗
NASA NTRS1971

Installation and integration of transonic transport propulsion systems.

Initial work indicates that a viable aircraft family can be designed for higher subsonic cruise speeds. Studies to date suggest that the propulsion system/nacelle design and the incorporation of noise attenuation into this design will have more influence on the choice of an optimum engine than engine weight and fuel consumption. These studies also suggest the payoff resulting from the incorporation of new technology items such as the internal engine generator and new structural cowl concepts because of the greater sensitivity to drag. These factors, plus the greater interdependency of the transonic aircraft and its propulsion system, point up the importance of a total system approach to propulsion system optimization and design.

Goodmanson, L. T.↗
NASA NTRS1971

Measurement of the propagating waves on Yagi-Uda array.

Measurement of the characteristics of the propagating waves on an array of identical wires. Experimental data showed that propagating waves could be supported on the structure without significant attenuation for two frequency bands. The central frequency of the higher passband was about three times higher tha n that of the lower passband. All propagating waves were slow waves. Phase velocities were varied from 0.99 to 0.25 of the free-space velocity. The k-beta diagrams of the waves were obtained and were found to be in good agreement with theory.

Cubley, H. D.↗
NASA NTRS1971

Radiative transfer effects on reflected shock waves. I - Transparent gas.

Analytical and numerical calculation of the effects of radiative cooling on the flow field and heat transfer behind a reflected shock wave. The analytical solutions are developed by an expansion procedure about the Newtonian limit - i.e., the flow variables are expanded in the small parameter epsilon representing the initial density ratio across the shock front. Solutions carried out through the zeroth- and first-orders in epsilon show an accuracy to the order of epsilon squared - namely, for the specific conditions considered the analytically calculated enthalpy changes agree to within 2% with the numerically computed changes. The numerical procedure consists of a finite-difference calculation with pressure gradients neglected. The analytical calculations show that pressure-gradient effects may be neglected, except at very long times when the shocked gas has cooled by a large amount. The present calculations show much greater shock-wave attenuation than does a previous numerical computation. This difference is attributed to a better representation of the thermodynamic properties in the present calculations.

Su, F. Y.↗
NASA NTRS1971

Effects of viscosity and constraints on the dispersion and dissipation of waves in large blood vessels. I.

Investigation of the effects of blood viscosity on dissipation as well as dispersion of small waves in arteries and veins by means of a parametric study. A linearized analysis of axisymmetric waves in a cylindrical membrane that contains a viscous fluid indicates that there are two families of waves: a family of slow waves and one of fast waves. The faster waves are shown to be more sensitive to variations in the elastic properties of the medium surrounding the blood vessels and at high values of the frequency parameter alpha. At low values of alpha the effects of viscosity on attenuation are reversed.

Jones, E.↗
NASA NTRS1971

Stress, fighting and neuroendocrine function.

Plasma concentrations of pituitary adrenocorticotrophic hormone (ACTH) and adrenocortical steroids in rats after testing in the shock-induced fighting paradigm were examined. The investigations provide data consistent with the view that psychological aspects of the stressful situation are important in determining the effects of shock on physiological function. The data indicate that the pituitary-adrenal response can be attenuated by the expression of an organized pattern of behavior.

Conner, R. L.↗
NASA NTRS1971

Trapping - A control phenomenon of spinning drag-free satellites.

A drag-free satellite contains a proof mass in an internal cavity and is controlled in translation so that it never touches the proof mass. The satellite shields the proof mass from external forces thus allowing the proof mass to follow a drag-free orbit. Spinning the satellite is desirable because it attenuates the effect of proof mass disturbing forces and simplifies the attitude control. The design of a translation controller for a spinning drag-free satellite typically includes a deadspace to eliminate chatter. This design feature and the inability to locate precisely the mass center give rise to a phenomenon called trapping that potentially could waste significant amounts of propellant. A theory is developed and experimentally verified that explains the role of these factors and provides insight into the effect of other control parameters.

Powell, J. D.↗
NASA NTRS1972

Gas physics environment of high altitude Jovian entry.

A description of the gas physics environment associated with high-altitude Jupiter entry is reported. Two aspects of environmental analysis are treated. First, limited discussion is devoted to prediction of the heating environment of the probe aeroshell. Prime emphasis is given to the second aspect of the analysis, a description of the gas particle probe interaction phenomena in the rarefied flow regime. Several molecular reemission models have been devised and exercised. Model selection was based upon the desire to bracket the expected reemission characteristics. Consideration was given to examining diffuse reflection as exemplified by the Maxwellian model and lobular, specular reflection as characterized by the Nocilla model. Variation of fundamental input parameters was investigated to determine particle-probe interaction sensitivity. Regardless of neutral species type, results show that the attenuation of the incoming flux of that species by reflected particles is approximately 15 per cent in the stagnation region at 200 km above the cloud tops.

Lefferdo, J. M.↗
NASA NTRS1972

Interaction of solar and galactic cosmic-ray particles with the moon.

Calculation of the rates of formation of radionuclides as a function of depth in the moon for bombardments by galactic-cosmic-ray particles and by solar protons. The fluxes and spectra of galactic-cosmic-ray particles and of solar protons as a function of depth in the moon are first determined semiempirically. For galactic cosmic rays, the model emphasizes the production of secondary particles and the attenuation of particles by nuclear interactions. Solar proton calculations cover a range of observed spectral parameters, and only ionization energy losses need be considered. The excitation functions for the nuclear reactions used in these calculations are presented. The calculated production rates are given for a range of depths in the moon and are compared with experimental results and with earlier calculations. The model can also be applied to other effects of particle bombardment.

Reedy, R. C.↗
NASA NTRS1972

Radiative transfer effects on reflected shock waves. II - Absorbing gas.

Radiative cooling effects behind a reflected shock wave are calculated for an absorbing-emitting gas by means of an expansion procedure in the small density ratio across the shock front. For a gray gas shock layer with an optical thickness of order unity or less the absorption integral is simplified by use of the local temperature approximation, whereas for larger optical thicknesses a Rosseland diffusion type of solution is matched with the local temperature approximation solution. The calculations show that the shock wave will attenuate at first and then accelerate to a constant velocity. Under appropriate conditions the gas enthalpy near the wall may increase at intermediate times before ultimately decreasing to zero. A two-band absorption model yields end-wall radiant-heat fluxes which agree well with available shock-tube measurements.

Su, F. Y.↗
NASA NTRS1971

Concepts and system design of a space emergency re-entry vehicle.

Discussion of the spectrum of remedial concepts and realistic mission constraints. A vehicle design is presented which is offered as the 'best' solution among a number of alternative designs in terms of its cost effectiveness. The probability of the safe reentry and recovery of one to three stranded astronauts is 0.80. The vehicle is symmetrical and lenticular in shape, and exhibits a modest lift-to-drag ratio of 0.5, allowing it to reenter a two-skip trajectory with minimal gravity forces on the astronauts. Attitude control, voice and beacon communication, and impact attenuation are also provided. The vehicle could be delivered in a docked position on the Apollo Applications Program multiple docking adapter.

Huang, C. J.↗
NASA NTRS1972

Cardiac beta-adrenergic receptors and coronary hemodynamics in the conscious dog during hypoxic hypoxia.

The mechanisms by which acute hypoxia (10% and 5% oxygen) mediates changes in coronary blood flow and cardiac function were investigated in the conscious dog. When the dogs breathed hypoxic gas mixtures through a tracheostomy, both arterial and coronary sinus oxygen tensions were significantly decreased. With 5% oxygen, there were significant increases in heart rate (25%), maximum left ventricular dP/dt (39%), left circumflex coronary artery blood flow (163%), and left ventricular oxygen consumption (52%), which were attenuated by beta-adrenergic blockage with propranolol. When electrical pacing was used to keep the ventricular rate constant during hypoxia, there was no significant difference in coronary blood flow before and after beta blockade. Beta-adrenergic receptor activity in the myocardium participates in the integrated response to hypoxia although it may not cause active vasodilation of the coronary vessels.

Erickson, H. H.↗
NASA NTRS1972

Development of four-dimensional atmospheric models and application techniques for space mission simulation.

The major objective of the four-dimensional atmospheric model program is to provide global profiles of moisture, temperature, pressure, and density from the surface to 25 km altitude. These models may then be used as input to the attenuation models for the purpose of simulating earth resource missions. Aspects of data processing are discussed together with homogeneous moisture regions, details regarding four-dimensional atmospheric models, and mission simulation procedures.-

Spiegler, D. B.↗