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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 1,639 records · Page 91
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Concurrent variation of response bias and sensitivity in an operant-psychophysical test.

The yes-no signal detection procedure was applied to a single-response operant paradigm in which rats discriminated between a standard auditory intensity and attenuated comparison values. The payoff matrix was symmetrical (with reinforcing brain stimulation for correct detections and brief time-out for errors), but signal probability and intensity differences were varied to generate a family of isobias and isosensitivity functions. The d' parameter remained fairly constant across a wide range of bias levels. Isobias functions deviated from a strict matching strategy as discrimination difficulty increased, although an orderly relation was maintained between signal probability value and the degree and direction of response bias.

Terman, M.↗
NASA NTRS1972

Material injection alleviation and plasma diagnostic measurements during the RAM C-III flight.

The results of a material injection RF blackout alleviation experiment and of plasma diagnostic measurements using electrostatic probes and an S-band reflectometer in a 25,000 ft/sec reentry flight are presented. Significant alleviation of RF blackout is observed at altitudes of from 270,000 feet to 120,000 feet due to injection of water and Freon E-3 on VHF, S-band, C-band, and X-band frequencies. Electrostatic probe data, attenuation data, and S-band diagnostic data show consistent plasma results. The relative effectiveness of water and Freon E-3 is discussed.

Schroeder, L. C.↗
NASA NTRS1972

Remote measurements of the atmosphere using Raman scattering.

Raman optical radar measurements of the atmosphere demonstrate that the technique may be used to obtain quantitative measurements of the spatial distribution of individual atmospheric molecular trace constituents (in particular water vapor) and of the major constituents. It is shown that monitoring Raman signals from atmospheric nitrogen aids in interpreting elastic scattering measurements by eliminating attenuation effects. In general, the experimental results show good agreement with independent meteorological measurements. Finally, experimental data are utilized to estimate the Raman backscatter cross section for water vapor excited at 3471.5 A.

Melfi, S. H.↗
NASA NTRS1972

Noise radiation from V/STOL aircraft.

This paper presents a detailed evaluation of design factors affecting noise annoyance by V/STOL aircraft. Community noise annoyance is quantified on the basis of recent analyses of survey data, and the implications on V/STOL design discussed. The effect of fundamental design choices on noise levels is analysed. The principal noise sources, and therefore the optimum noise control measures, are a function of disc loading. It is found that increase in rotor scale gives a substantial benefit in subjective levels at the lower disc loadings. Rotor noise source mechanisms are discussed in detail and the dominant effect of the unsteady aerodynamic input to the rotor demonstrated. Data on the effects of recirculation on noise is presented. Two approaches for low noise V/STOL seem to be feasible. These are the low disc loading open rotor, and a ducted fan with substantial duct attenuation treatment. The principal noise control methods for each approach are given.

Lowson, M. V.↗
NASA NTRS1972

Techniques in balloon X-ray astronomy.

Since the first balloon observation of the Crab Nebula balloon data have provided much information on the positions, spectra, time variability and pulsed nature of localized sources, and on the spectrum and isotropy of diffuse galactic and universal components. Measurements are limited to energies above about 20 keV by atmospheric attenuation at 2 to 3 g/sq cm depth and to below several hundred keV by detector sensitivity. Detectors usually consist of large-area Na I or Cs I scintillation counters with anticoincidence collimators for rejection of charged particles and scattered X-rays. Proportional counters are occasionally used at lower energies and solid-state detectors are used where extreme energy resolution is important. The instruments require a pointing capability on the order of 1.0 to 0.1 deg, depending on the collimator aperture. Digital data is either recorded on board or telemetered using a PCM technique.

Peterson, L. E.↗
NASA NTRS1962

Proceedings of the Symposium on the Protection Against Radiation Hazards in Space Book 1: Radiation Environment in Space. Effects of Space Radiation on Radio Sensitive Objects. Biological Effects of Space Radiation

The realization in recent years that outer space is traversed by high-energy radiations has caused man to reevaluate the feasibility of manned or even instrumented exploration outside our atmosphere. Fortunately, it is possible to determine the nature and intensities of these radiations and to produce similar radiations on earth by means of accelerators. Thus we can learn how to attenuate them and to design capsules which afford protection against them. Of course this protection carries a weight penalty so that there is a premium on optimizing the shield design. Many groups in the United states are engaged in research to this end,and it was the purpose of this symposium to bring these groups together so that they could exchange information. To make the meeting more comprehensive, sessions on the nature of the radiations and their effects on people and things were included. However, the major part of the meeting was devoted to discussions on shielding research, comprising theoretical calculations and experiments carried out mainly with high-energy accelerators. The symposium committee feels that the aims of the symposium were met and that progress in space research program was greatly accelerated thereby.

Source record↗
NASA NTRS1973

Extended range harmonic filter

Two types of filters, leaky-wall and open-guide, are combined into single component. Combination gives 10 db or greater additional attenuation to fourth and higher harmonics, at expense of increasing loss of fundamental frequency by perhaps 0.05 to 0.08 db. Filter is applicable to all high power microwave transmitters, but is especially desirable for satellite transmitters.

Jankowski, H.↗
NASA NTRS1973

Integral aircraft passenger seat

Human-engineering approach was used to design integral seat which provides all the safety, comfort, and protective features that can possibly be afforded airline passengers. Results of dynamic impact testing indicated that seat can withstand and attenuate gravity loads of 21-g horizontal and 45-g vertical; by design, seat will withstand lateral g's as well.

Kubokawa, C. C.↗
NASA NTRS1972

Flow conditions around the exit and downstream of certain stator blading with various trailing edge thicknesses and geometries

The blading investigated was curved back with thick profiles. The variations in flow conditions considered were flow angle and isentropic energy. Experimental data were obtained in a two-dimensional cascade from surveys with a combined angle, total-, and static-pressure probe and from an array of end-wall static pressure taps. Analytical results were obtained from ideal flow theory. The results showed large variations in flow conditions close to the plane of the trailing edge that were largely attenuated at a distance a little greater than one blade pitch downstream of the trailing edge in the direction of flow. The results were affected by the geometry and thickness of the trailing edge. The agreement between experimental and analytical results is generally fair to excellent.

Prust, H. W., Jr.↗
NASA NTRS1972

The influence of polarization on millimeter wave propagation through rain

A program for the measurement and analysis of the depolarization and differential attenuation that occur when millimeter wave signals propagate through rain is described. Initial data are taken along a 1.43 km path at 17.65 GHz and a supporting theoretical model is developed to relate the propagation effects to rainfall rate and wind velocity. A block diagram of the overall experiment is included. It consists of: (1) an RF system (millimeter wave transmitter and receiver), (2) transmitting and receiving antennas, (3) a weather system with rain gauges, wind sensors, and drop counters, and (4) a digital control, processing, and data storage system.

Bostian, C. W.↗
NASA NTRS1972

Power spectra of the interplanetary magnetic field near the earth

Power spectra of the interplanetary magnetic field measured by near-earth satellites upstream from the earth's bow shock are free from terrestrial contamination provided the field at the satellite does not intersect the bow shock. Considerable spectral enhancement for the range of frequencies 0.01 to 1.00 Hz, due to turbulence caused by the shock, may occur if the field observed at the satellite intersects the shock. This turbulence occurs frequently in both the morning and afternoon quadrants. In the frequency band from 0.07 to 1 Hz, this noise decreases in amplitude with radial distance from the shock with an attenuation length of 4 R sub E.

Childers, D. D.↗
NASA NTRS1972

Acoustic results obtained with upper-surface-blowing lift augmentation systems

The noise caused by the interaction of the jet exhaust and a wing was measured under static conditions for several versions of a small-scale STOL engine-over-the-wing configuration. Three basic nozzles were used in the tests; a circular nozzle, a 5:1 aspect ratio slot nozzle and a 10:1 aspect ratio slot nozzle. Various flow attachment devices were included in the study. The wing included a flap that could be positioned for nominal takeoff or approach flap settings. Far field noise data are presented for the flyover mode. The data are discussed in terms of sound power and sound pressure spectra. Implications of extending the small-scale model acoustic data to full-scale aircraft are discussed briefly and indicate a sizeable flyover noise attenuation may be achieved due to shielding by the wing.

Vonglahn, U. H.↗
NASA NTRS1972

A review of some aspects of inferring the ozone profile by inversion of ultraviolet radiance measurements

The mathematical inversion of light-scattering observations to obtain the atmospheric ozone profile is discussed in terms of the filtering properties of the physical and mathematical processes for different spatial scales. Within this context, it is shown that the physical process of scattering acts as a low pass filter; which transfers large-scale profile information efficiently to radiance observations but very strongly attenuates small- or fine-scale profile information. To avoid domination of the mathematical inversion by the random error of radiance measurements, an equivalent spatial-scale filtering in the inversion procedure is essential. The available evidence suggests that mathematical inversion to obtain the low level ozone profile below 25 to 30 km is either inferior to or no better than the statistical estimation of the profile using total ozone as predictor. However, inversion profiles for high level ozone above 25 to 30 km appear to have moderately good accuracy.

Mateer, C. L.↗
NASA NTRS1972

Lidar probing of the atmosphere: Some quantitative aspects

Lidar uses laser energy in radar fashion to observe atmospheric backscattering as a function of range. Because of the short optical and near-optical wavelengths used, very small particles and even the gaseous molecules cause significant scattering. This can complicate the evaluation of the observations by introducing attenuation along the path as a second unknown into the lidar equation. In many cases, however, the observations may be interpreted directly on a qualitative basis and show the distribution of particulate matter in clear air or enable the dimensions of visible cloud to be measured accurately. In other cases, particularly where additional data are available, quantitative solutions can provide useful information on remote targets such as tenuous smoke clouds or haze layers. Examples of such observations are given, illustrating the computational approach to the evaluation of the volume concentration of natural dust and haze layers in the lower atmosphere and the mass concentration of a smoke plume. In both cases lidar data are related to independently obtained data on the particulate concentrations involved.

Collis, R. T. H.↗
NASA NTRS1972

Analysis of propellant feedline dynamics

An analytical model and computer program were developed for studying the disturbances of liquid propellants in engine feedline systems. It was found that the predominant effect of turbulence is to increase the spatial attenuation at low frequencies; at high frequencies the laminar and turbulent frequencies coincide. Recommendations for future work are included.

Astleford, W. J.↗
NASA NTRS1972

Fan noise suppression

The principal suppressor parameters and their relationships have been used to formulate a suppressor design methodology which has been applied to the design of several full-scale suppressors. Tests of these suppressors on several full-scale fans have demonstrated noise reductions of the order of 10 PNdB. The amount of suppression in several instances seems to have been limited by reaching noise floors that are not clearly at the estimated jet noise level but are not far above it. In addition to identifying noise floors, two other areas are considered. The first is attenuation by the fan exhaust suppressors, which seems in most cases to be less than that of the inlet. The second is the effectiveness of outer cowl treatment alone on multiple pure tones. This question relates to whether a high-speed fan can become as quiet as a low-speed fan without a substantial increase in the amount of treatment.

Feiler, C. E.↗
NASA NTRS1972

Design study of an air pump and integral lift engine ALF-504 using the Lycoming 502 core

Design studies were conducted for an integral lift fan engine utilizing the Lycoming 502 fan core with the final MQT power turbine. The fan is designed for a 12.5 bypass ratio and 1.25:1 pressure ratio, and provides supercharging for the core. Maximum sea level static thrust is 8370 pounds with a specific fuel consumption of 0.302 lb/hr-lb. The dry engine weight without starter is 1419 pounds including full-length duct and sound-attenuating rings. The engine envelope including duct treatment but not localized accessory protrusion is 53.25 inches in diameter and 59.2 inches long from exhaust nozzle exit to fan inlet flange. Detailed analyses include fan aerodynamics, fan and reduction gear mechanical design, fan dynamic analysis, engine noise analysis, engine performance, and weight analysis.

Rauch, D.↗
NASA NTRS1972

Analyses of solar viewing time, beta angle, and doppler shift for solar observations from the space shuttle

Studies of solar physics phenomena are aided by the ability to observe the sun from earth orbit without periodic occultation. Charts are presented for the selection of suitable orbits about the earth at which a spacecraft is continuously illuminated through a period of a few days. Selection of the orbits considers the reduction of Doppler shift and wavefront attenuation due to relative orbital velocity and residual earth atmosphere.

Brandon, J. P.↗