Engineering Papers⌕ Search

SEARCH · Engineering Papers

Results for “Transducers”

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.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 1,675 records · Page 93
All sourcesNASA NTRSDOE OSTI
NASA NTRS1975

Diode-quad bridge circuit means

A transducer and frequency discriminator circuit is described including a four-terminal circulating diode bridge, a first pair of capacitors connected in series across two terminals of the bridge, and a second pair of capacitors, or other impedance elements, connected in series across the other two terminals of the bridge. A source of balanced alternating electrical energy for energizing the circuit is coupled between the commonly connected plates of the first pair of capacitors and the commonly connected plates of the second pair of capacitors. Due to the operation of the diode bridge, the sum of the resultant charges developed on the first pair of capacitors is proportional to the relationship between the respective capacitors of the second pair, and consequently, an output voltage taken across the first pair of capacitors will be proportional to that relationship.

Harrison, D. R.↗
NASA NTRS1975

An experimental investigation of compressor stall using an on-line distortion indicator and signal conditioner

The relation of the steady-state and dynamic distortions and the stall margin of a J85-13 turbojet engine was investigated. A distortion indicator capable of computing two distortion indices was used. A special purpose signal conditioner was also used as an interface between transducer signals and distortion indicator. A good correlation of steady-state distortion and stall margin was established. The prediction of stall by using the indices as instantaneous distortion indicators was not successful. A sensitivity factor that related the loss of stall margin to the turbulence level was found.

Costakis, W. G.↗
NASA NTRS1974

Attitude Control Propulsion Components, Volume 2

Attitude control propulsion components are described, including hydrazine thrusters, hydrazine thruster and cold gas jet valves, and pressure and temperature transducers. Component-ordered data are presented in tabular form; the manufacturer and specific space program are included.

Source record↗
NASA NTRS1975

Diode-quad bridge circuit means

Diode-quad bridge circuit means is described for use as a transducer circuit or as a discriminator circuit. It includes: (1) a diode bridge having first, second, third, and fourth bridge terminals consecutively coupled together by four diodes polarized in circulating relationship; (2) a first impedance connected between the second bridge terminal and a circuit ground; (3) a second impedance connected between the fourth bridge terminal and the circuit ground; (4) a signal source having a first source terminal capacitively coupled to the first and third bridge terminals, and a second source terminal connected to the circuit ground; and (5) an output terminal coupled to the first bridge terminal and at which an output signal may be taken.

Harrison, D. R.↗
NASA NTRS1975

Investigation of space shuttle vehicle 140C configuration orbiter (model 16-0) wheel well pressure loads in the Rockwell International 7.75 x 11 foot wind tunnel (OA143)

Experimental aerodynamic investigations were conducted on a sting mounted .0405-scale representation of the 140C outer mold line space shuttle orbiter configuration in the Rockwell International 7.75 x 11.00 foot low speed wind tunnel. The primary test objectives were to define the orbiter wheel well pressure loading and its effects on landing gear thermal insulation and to investigate the pressure environment experienced by both the horizontal flight nose probe and air vent door probes. Steady state and dynamic pressure values were recorded in the orbiter nose gear well, left main landing gear well, horizontal flight nose probe, and both left and right air vent door probe. All steady state pressure levels were measured by Statham differential pressure transducers while dynamic pressure levels were recorded by Kulite high frequency response pressure sensors.

Mennell, R. C.↗
NASA NTRS1975

Monitoring crack extension in fracture toughness tests by ultrasonics

An ultrasonic method was used to observe the onset of crack extension and to monitor continued crack growth in fracture toughness specimens during three point bend tests. A 20 MHz transducer was used with commercially available equipment to detect average crack extension less than 0.09 mm. The material tested was a 300-grade maraging steel in the annealed condition. A crack extension resistance curve was developed to demonstrate the usefulness of the ultrasonic method for minimizing the number of tests required to generate such curves.

Klima, S. J.↗
NASA NTRS1975

Study of noise sources in a subsonic fan using measured blade pressures and acoustic theory

Sources of noise in a 1.4 m (4.6 ft) diameter subsonic tip speed propulsive fan running statically outdoors are studied using a combination of techniques. Signals measured with pressure transducers on a rotor blade are plotted in a format showing the space-time history of inlet distortion. Study of these plots visually and with statistical correlation analysis confirms that the inlet flow contains long, thin eddies of turbulence. Turbulence generated in the boundary layer of the shroud upstream of the rotor tips was not found to be an important noise source. Fan noise is diagnosed by computing narrowband spectra of rotor and stator sound power and comparing these with measured sound power spectra. Rotor noise is computed from spectra of the measured blade pressures and stator noise is computed using the author's stator noise theory. It is concluded that the rotor and stator sources contribute about equally at frequencies in the vicinity of the first three harmonics of blade passing frequency. At higher frequencies, the stator contribution diminishes rapidly and the rotor/inlet turbulence mechanism dominates. Two parametric studies are performed by using the rotor noise calculation procedure which was correlated with test. In the first study, the effects on noise spectrum and directivity are calculated for changes in turbulence properties, rotational Mach number, number of blades, and stagger angle. In the second study the influences of design tip speed and blade number on noise are evaluated.

Hanson, D. B.↗
NASA NTRS1975

Electrical and electronic devices and components: A compilation

Components and techniques which may be useful in the electronics industry are described. Topics discussed include transducer technology, printed-circuit technology, solid state devices, MOS transistors, Gunn device, microwave antennas, and position indicators.

Source record↗
NASA NTRS1975

Development of a dynamic pressure calibration technique

The report deals with work continuing on the development of a method of producing sinusoidally varying pressures of at least 34 kPa zero-to-peak with amplitude variations within plus or minus 5% up to 2 kHz for the dynamic calibration of pressure transducers. Sinusoidally varying pressures of 34 kPa zero-to-peak were produced between 40 Hz and 750 Hz by vibrating a 10-cm column of a dimethyl siloxane liquid at 36gn zero-to-peak. Damping of the liquid column was accomplished by packing the fixture tube with a number of smaller diameter tubes.

Vezzetti, C. F.↗
NASA NTRS1974

Automated measurement of respiratory gas exchange by an inert gas dilution technique

A respiratory gas analyzer (RGA) has been developed wherein a mass spectrometer is the sole transducer required for measurement of respiratory gas exchange. The mass spectrometer maintains all signals in absolute phase relationships, precluding the need to synchronize flow and gas composition as required in other systems. The RGA system was evaluated by comparison with the Douglas bag technique. The RGA system established the feasibility of the inert gas dilution method for measuring breath-by-breath respiratory gas exchange. This breath-by-breath analytical capability permits detailed study of transient respiratory responses to exercise.

Sawin, C. F.↗
NASA NTRS1975

Experimental evaluation of trailing edge and incidence fluctuation noise theories

Tests were conducted to evaluate conflicting theories for trailing edge noise and for incidence fluctuation noise. A flat-plate airfoil with flush-mounted surface pressure transducers was tested in an anechoic wind tunnel at velocities from 31.5 to 177 m/sec and nominal 4 and 6% grid-generated turbulence levels. In one series of runs, the airfoil was faired into the tunnel nozzle and extended beyond the nozzle lip for studies of trailing edge noise without a leading edge and with flow on only one side. Such noise was found to vary with velocity to the fifth power and turbulence level squared as predicted by Ffowcs Williams and Hall (1970) and by Chase (1972). Power spectral density at high frequencies decayed approximately inversely with frequency to the 10/3 power as predicted by Chase. The data were poorly predicted by Hayden's correlation (1969, 1972).

Fink, M. R.↗
NASA NTRS1975

Quantitative density visualization in a transonic rotor

The flow in a two foot diameter transonic rotor has been visualized using a fluorescent gas, 2, 3 butanedione, as a tracer. The technique allows the three dimensional flow to be imaged as a set of distinct planes. Quantitative static density maps can be obtained after correcting the images for distortion and nonlinearities introduced by the illumination and imaging systems. The visualized flow is compared to data taken simultaneously by high frequency pressure transducers near the rotor entrance and exit planes.

Epstein, A. H.↗
NASA NTRS1975

A high altitude base pressure experiment

A high-altitude base-pressure experiment has been successfully conducted on a high-performance Air Force reentry vehicle. Low Reynolds number laminar-flow flight data were obtained at an altitude of about 248,000 ft. The experiment utilized the NASA Ames vibrating diaphragm transducer specifically designed to measure base pressure at altitudes in excess of 200,000 ft with a threshold sensitivity level of 0.0002 psia. The flight data have provided needed low Reynolds number information from Reynolds numbers of about 70,000 to 10,000,000. These new data verify that a 'maximum' exists in the base pressure ratio versus Reynolds number curve at low Reynolds numbers and hypersonic Mach numbers (free-stream Mach numbers greater than 20) in qualitative agreement with the theory of Crooco and Lees (1952).

Cassanto, J. M.↗
NASA NTRS1975

Electro-optical processing of phased-array antenna data

An on-line two-dimensional optical processor has been used to process simulated linear and planar phased-array radar data off-line but at real-time data rates. The input transducer is an electron-beam-addressed KD2PO4 light valve.

Casasent, D.↗
NASA NTRS1975

Preliminary measurements of plasma fluctuations in an 8-cm mercury ion thruster

The investigation considered included an observation of the effects on the plasma fluctuations of a variation of several neutralizer parameters. The apparatus used in the investigation and the experimental techniques are discussed, taking into account the thruster, the thruster power supply, questions of thruster operation, transducers, and an analysis of time-varying data. The results presented are related to rms magnitudes, spectral data, and fluctuation correlations.

Serafini, J. S.↗
NASA NTRS1975

A study of subsonic fan noise sources

Sources of noise in a 1.4 m (4.6 ft) diameter subsonic tip speed propulsive fan were studied using a combination of theoretical, experimental, and computer plotting techniques developed specially for noise diagnosis. To assess the structure of inlet turbulence, signals measured from pressure transducers on a rotor blade were plotted in a format to show the space-time history of inlet distortion. Ingested turbulence contained long, thin eddies which produce a tone-like noise component. Turbulence generated in the shroud boundary layer upstream of the rotor tips was found not to be an important noise source. However, this boundary layer does contain large amplitude disturbances caused by inlet turbulence which could be important in fans with thicker boundary layers. Theoretical calculations based on measured blade pressures show that rotor/inlet turbulence interaction and rotor/stator interaction are equally important sources of noise near the first three harmonics of blade passing frequency. At higher frequencies (above 2000 Hz) the rotor noise is dominant.

Hanson, D. B.↗
NASA NTRS1975

An optical/digital processor - Hardware and applications

A real-time two-dimensional hybrid processor consisting of a coherent optical system, an optical/digital interface, and a PDP-11/15 control minicomputer is described. The input electrical-to-optical transducer is an electron-beam addressed potassium dideuterium phosphate (KD2PO4) light valve. The requirements and hardware for the output optical-to-digital interface, which is constructed from modular computer building blocks, are presented. Initial experimental results demonstrating the operation of this hybrid processor in phased-array radar data processing, synthetic-aperture image correlation, and text correlation are included. The applications chosen emphasize the role of the interface in the analysis of data from an optical processor and possible extensions to the digital feedback control of an optical processor.

Casasent, D.↗
NASA NTRS1975

Effect of varying differentiator frequency response on recorded peak dP/dt

Dogs were used to study the effects of varying the differentiator cutoff frequency on the recorded peak first derivative of left ventricular pressure with respect to time (dP/dt), using high-precision solid-state pressure transducers and recording equipment. In canine hearts with a basic periodicity of 1 to 3 Hz, the differentiator frequency response required to record an accurate peak dP/dt is found to be influenced by the value of peak dP/dt. At peak dP/dt ranging from 1500 to 9000 mm Hg/sec (200 and 1200 kPa/sec), a differentiator cutoff frequency of at least 90 Hz was required to record accurately peak dP/dt.

Barry, W. H.↗