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  • Other Sources  (556)
  • AERODYNAMICS  (366)
  • ELECTRONICS AND ELECTRICAL ENGINEERING  (190)
  • Animals
  • 1980-1984  (556)
  • 1925-1929
  • 1981  (556)
  • 1
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    Curved-flow, rolling-flow, and oscillatory pure-yawing wind-tunnel test methods for determination of dynamic stability derivatives (1981)
    In:  CASI
    Details
    Publication Date: 2011-10-14
    Description: The test capabilities of the Stability Wind Tunnel of the Virginia Polytechnic Institute and State University are described, and calibrations for curved and rolling flow techniques are given. Oscillatory snaking tests to determine pure yawing derivatives are considered. Representative aerodynamic data obtained for a current fighter configuration using the curved and rolling flow techniques are presented. The application of dynamic derivatives obtained in such tests to the analysis of airplane motions in general, and to high angle of attack flight conditions in particular, is discussed.
    Keywords: AERODYNAMICS
    Type: AGARD Dyn. Stability Parameters; 13 p
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  • 2
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    A BAPTA employing rotary transformers, stepper motors and ceramic ball bearings (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The utilization of rotary transformers as an alternative to slip rings for the power transfer from solar panels to a satellite's main body could be advantageous, especially if an ac bus system is taken into consideration. Different approaches with main emphasis on the electromagnetic design were investigated and showed efficiencies of up to 99% with a 3 kW power capability. A solidly preloaded pair of ball bearings with ceramic balls assures proper transformer air gaps and acceptable torque changes over temperature and temperature gradients. The bearing and power transfer assembly is driven by a direct drive stepper motor with inherent redundancy properties and needs no caging mechanism.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 189-203
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  • 3
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    An analytic solution to the classical two-body problem with drag (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The two body problem was analyzed with a specific drag model. The model treats drag as a force proportional to the vector velocity and inversely proportional to the distance to the center of attraction. The solution is expressed in terms of known functions and is of a simple and compact form. The time of flight is expressed as a quadrature in the true anomaly. The results are: (1) development of a vector differential equation which allows analysis of an infinite number of gravitational and drag models; and (2) obtaining the solution of a linear differential equation using the inverse method of laplace transforms.
    Keywords: AERODYNAMICS
    Type: Houston Univ. The 1981 NASA ASEE Summer Fac. Fellowship Program, Vol. 2; 22 p
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  • 4
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    Langley high-lift research on a high-aspect-ratio supercritical wing configuration (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: To determine the low speed performance characteristics of a representative high aspect ratio supercritical wing, two low speed jet transport models were fabricated. A 12-ft. span model was used for low Reynolds number tests in the Langley 4- by 7-Meter Tunnel and the second, a 7.5-ft. span model, was used for high Reynolds number tests in the Ames 12-foot Pressure Tunnel. A brief summary of the results of the tests of these two models is presented and comparisons are made between the data obtained on these two models and other similar models. Follow-on two and three dimensional research efforts related to the EET high-lift configurations are also presented and discussed.
    Keywords: AERODYNAMICS
    Type: Advan. Aerodyn.: Selected NASA Res.; p 55-77
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  • 5
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    Measured transonic unsteady pressures on an energy efficient transport wing with oscillating control surfaces (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Highlight results are presented from subsonic and transonic pressure measurement studies conducted in the Langley Transonic Dynamics Tunnel on a supercritical wing model representative of an energy efficient transport design. Steady- and unsteady-pressure data were acquired on the upper and lower wing surface at an off-design Mach number of 0.60 and at the design Mach number of 0.78, for a Reynolds number of 2.2 x 10(6) (based on the wing average chord). The model configuration consisted of a sidewall-Mounted half-body fuselage and a semi-span wing with an aspect ratio of 10.76, a leading-edge sweepback angle of 28.8 degrees, and supercritical airfoil sections. The wing is instrumented with 252 static pressure orifices and 164 dynamic pressure gages. Model test variables included wing angle of attack, control-surface mean deflection angle, control-surface oscillating deflection angle and frequency, and phasing between oscillating leading-edge and trailing-edge controls when used together.
    Keywords: AERODYNAMICS
    Type: Advan. Aerodyn.: Selected NASA Res.; p 21-36
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  • 6
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    Vortex-flow aerodynamics - An emerging design capability (1981)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Promising current theoretical and simulational developments in the field of leading edge vortex-generating delta, arrow ogival wings are reported, along with the history of theory and experiment leading to them. The effects of wing slenderness, leading edge nose radius, Mach number and incidence variations, and planform on the onset of vortex generation and redistribution of aerodynamic loads are considered. The range of design possibilities in this field are consequential for the future development of strategic aircraft, supersonic transports and commercial cargo aircraft which will possess low-speed, high-lift capability by virtue of leading edge vortex generation and control without recourse to heavy and expensive leading edge high-lift devices and compound airfoils. Attention is given to interactive graphics simulation devices recently developed.
    Keywords: AERODYNAMICS
    Type: Astronautics and Aeronautics; 19; May 1981
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  • 7
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    Longitudinal grooves for bluff body drag reduction (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Wind tunnel test results are presented for four axisymmetric bluff body configurations in order to determine their effect on form and pressure drag. It was found that drag reductions on the order of 40% are obtainable with an afterbody incorporating four longitudinal 'V' grooves. Although this effect may be due to the functioning of the grooves as longitudinal, continuous vortex generators, it is concluded that further research is needed to elucidate the physical basis of the test results. Optimization of the effect will be useful in base drag reduction for such vehicles as automobiles and cargo aircraft with sharply upswept afterbodies.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Apr. 198
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  • 8
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    Near millimeter wave bandpass filters (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The properties of bandpass filters for broadband photometry are reported in the 3-12/cm frequency range. The filters are based on a combination of capacitive grids deposited on thick Mylar substrates and are designed to have very high out-of-band rejection. Low frequencies are blocked by a thick grill that consists of a hexagonal grid of circular holes in a thick metal plate.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Applied Optics; 20; Apr. 15
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  • 9
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    Vectored injection into compressible laminar and turbulent boundary layers (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A fundamental analysis of two-dimensional supersonic boundary layer flow, both laminar and turbulent, is presented for a wide range of normal and nonnormal mass-transfer velocities. The analysis is based on the numerical solution of the Navier-Stokes equations, and results are compared with available theoretical and experimental data. Certain cases of practical importance, for which results are not presently available, are referred to.
    Keywords: AERODYNAMICS
    Type: Computer Methods in Applied Mechanics and Engineering; 25; Jan. 198
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  • 10
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    Report of the panel on theoretical aerodynamics (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Interactions between theoretical aerodynamics and the NTF are discussed. The development and validation of computational fluid dynamics computer codes, the determination of Reynolds number scaling laws, and extension of the data bases of entrainment type turbulence models to include high Reynolds number data are recommended areas of study. The major benefit theoretical aerodynamics could have on the NTF is in the quantitative description of wind tunnel wall interference effects.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 277-286
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  • 11
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    High Reynolds number research requirements for space vehicle design (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Requirements of entry vehicle design requiring high Reynolds number wind tunnel testing are discussed. The space shuttle orbiter, development of future space transportation systems, and planetary entry data analysis are considered.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 265-274
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  • 12
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    Report of the panel on aeroelasticity and unsteady aerodynamics (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The status of recommended areas of study for the NTF are reviewed. Transonic and control surface unsteady aerodynamics, and buffet onset and loads are considered. Testing of dynamically scaled flutter models is discussed.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 237-246
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  • 13
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    Model experience in the Langley 0.3-m transonic cryogenic tunnel (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The model building, development, and testing experience gained during 8 years of operation of the 0.3-m Transonic Cryogenic Tunnel (TCT) is summarized. The summary is divided into four portions: (1) models tested in the 0.3-m TCT's original octagonal test section; (2) models tested in the present two dimensional test section; (3) models tested as a part of tunnel calibration and the development of advanced technology airfoils; and (4) development of a new way to construct two dimensional airfoil models. Design requirements imposed on the models by high Reynolds number testing at cryogenic temperatures are reviewed.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 53-73
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  • 14
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    Coherent reference generator phase stability (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Approximate phase stability estimates for the coherent reference generator (CRG) unit in the DSN's Frequency and Timing Subsystem (FTS) are calculated. The method used involves estimating the phase noise introduced by CRG components based upon measurements made in the past on similar components in other parts of the FTS and obtaining the CRG phase noise from the component phase noises. Three estimates of phase stability are calculated: the fractional frequency change for a 5 C step in temperature, the phase noise spectral density, and the Allan standard deviation. It is found from these estimates that the CRG phase stability is better than that of the H-maser physics unit + receiver. Thus, the first step in improving FTS phase stability would be to make improvements in the H-maser physics unit + receiver. These results are corroborated by indirect clock stability estimates calculated from Doppler data.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Progr. Rept. 42-64; p 222-231
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  • 15
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    Second-generation X/S feedcone: Capabilities layout, and components (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: High power (20 kW) S and X-band transmitting systems were added to the Second Generation Common Aperture X/S Feedcone System to demonstrate X and S band uplink/downlink capabilities. Design considerations of new X band components, cone layout, and capabilities are discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 97-103
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  • 16
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    End-to-end quality measure for transmission of compressed imagery over a noisy coded channel (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: For the transmission of imagery at high data rates over large distances with limited power and system gain, it is usually necessary to compress the data before transmitting it over a noisy channel that uses channel coding to reduce the effect of noise introduced errors. Both compression and channel noise introduce distortion into the imagery. In order to design a communication link that provides adequate quality of received images, it is necessary first to define some suitable distortion measure that accounts for both these kinds of distortion and then to perform various tradeoffs to arrive at system parameter values that will provide a sufficiently low level of received image distortion. The overall mean square error is used as the distortion measure and a description of how to perform these tradeoffs are included.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Telecommun. and Data Acquisition; p 63-72
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  • 17
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    Effectiveness of leading-edge vortex flaps on 60 and 75 degree delta wings (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A series of wind tunnel tests were run on 60 and 75 deg sweep delta wings to examine the effectiveness of leading-edge vortex flaps. Tests results showed that leading-edge vortex flaps are effective in giving large increases in lift-to-drag ratio and decreases in drag over a wide range of angle of attack. Tests on inverted flaps on the 60 deg delta wing showed substantial increases in lift and drag and may indicate a possibility of using inverted flaps on delta wings in the landing portion of flight. The 60 deg data were compared with that for a 75 deg sweep delta wing confirming that leading-edge vortex flap effectiveness is stronger as sweep is increased. Pitching moment effects due to vortex flaps use were also examined.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 18; Apr. 198
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  • 18
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    Semiconductor-ferroelectric nonvolatile memory using anomalous high photovoltages in ferroelectric ceramics (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A small ferroelectric ceramic element is used with an insulating gate transistor and two diodes as an electrically addressed, nonvolatile memory device which is read out nondestructively. The device uses the anomalous photovoltaic effect in ferroelectric ceramics, an effect in which the polarity and magnitude of photovoltages depend on the direction and magnitude of remanent polarization. Experimental results give memory characteristics. The device could be programmed with pulses as short as 200 ns. There is long-time retention of stored data.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Applied Physics Letters; 38; Feb. 1
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  • 19
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    Partially confined multiple jet mixing (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Results of hot-wire measurements in an incompressible partially confined jet issuing from an array of rectangular nozzles, equally spaced with their small dimensions aligned are presented. The quantities measured include mean velocity and the Reynolds stress in the two central planes of the jet at stations covering up to 115 widths (small dimension of a nozzle) downstream of the nozzle exit. For downstream distances greater than 60 widths, the flowfield is observed to be nearly homogenous and the turbulence appears to be quite similar to that of a grid generated turbulence.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Mar. 198
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  • 20
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    Unsteady Newton-Busemann flow theory. I - Airfoils (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Newtonian flow theory for unsteady flow at very high Mach numbers is completed by the addition of a centrifugal force correction to the impact pressures. The correction term is the unsteady counterpart of Busemann's centrifugal force correction to impact pressures in steady flow. For airfoils of arbitary shape, exact formulas for the unsteady pressure and stiffness and damping-in-pitch derivatives are obtained in closed form, which require only numerical quadratures of terms involving the airfoil shape. They are applicable to airfoils of arbitrary thickness having sharp or blunt leading edges. For wedges and thin airfoils these formulas are greatly simplified, and it is proved that the pitching motions of thin airfoils of convex shape and of wedges of arbitrary thickness are always dynamically stable according to Newton-Busemann theory. Leading-edge bluntness is shown to have a favorable effect on the dynamic stability; on the other hand, airfoils of concave shape tend toward dynamic instability over a range of axis positions if the surface curvature exceeds a certain limit. As a byproduct, it is also shown that a pressure formula recently given by Barron and Mandl for unsteady Newtonian flow over a pitching power-law shaped airfoil is erroneous and that their conclusion regarding the effect of pivot position on the dynamic stability is misleading.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Mar. 198
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  • 21
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    Evidence of imbedded vortices in a three-dimensional shear flow (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Vortex phenomena encountered in an investigation of the streamwise development of the three-dimensional wake region behind the tip of a three-dimensional wedge model are reported. Pressure profiles were measured by pitot probes downstream of a tip with a nearly constant surface pressure level and a nearly continuous surface curvature in a blowdown air tunnel operating at Mach 6. Rather than the simple three-dimensional quasi-parallel shear flow expected, the measurements indicated the presence of a flow with large deficits in longitudinal pitot pressure, which are usually associated with the core region of quasi-steady longitudinal vortices. Vapor screen flow visualizations also support the presence of longitudinal vortices located primarily in the tip region and evidently forming in the vicinity of the wake neck. An increase in overall wake thickness by 100% is also observed. The origin of the vortices as quasi-steady Taylor-Gortler vortices generated in the concavely curved shear layer near the wake neck is considered. It is pointed out that the existence of longitudinal vortexes suggests that three-dimensional turbulence modeling may be much more difficult than previously supposed.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Mar. 198
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  • 22
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    Optically induced bistable states in metal/tunnel-oxide/semiconductor /MTOS/ junctions (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A new switching phenomenon in metal-oxide semiconductor tunnel junction has been discovered. With a sufficiently large negative bias applied to the electrode, incident visible light of intensity greater than about 1 microW/sq cm causes the reverse-biased junction to switch from a low-current to a high-current state. It is believed that hot-electron-induced impact ionization provides the positive feedback necessary for switching, and causes the junction to remain in its high-current state after the optical excitation is removed. The junction may be switched back to the low-current state electrically. The basic junction characteristics have been measured, and a simple model for the switching phenomenon has been developed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Applied Physics Letters; 38; Jan. 1
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  • 23
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    The millimeter wave super-Schottky diode detector (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The 31 and 92 GHz measurements of the superconductor-Schottky diode extended to millimeter wavelengths by a redesign of the semiconductor interface are reported. Diodes were fabricated by pulse electroplating Pb on 2 x 10 to the 19th/cu cm p-Ga-As etched with HCl; a thin Au overplate is deposited to protect the Pb film from degradation and to improve its lifetime. The noise performance was almost ideal at 31 and 92 GHz; it was concluded that this diode is a quantum-limited-detector at 31 GHz, with excessive parasitic losses at 92 GHz.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 24
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    Proposed aeroelastic and flutter tests for the National Transonic Facility (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Tests that can exploit the capability of the NTF and the transonic cryogenic tunnel, or lead to improvements that could enhance testing in the NTF are discussed. Shock induced oscillation, supersonic single degree control surface flutter, and transonic flutter speed as a function of the Reynolds number are considered. Honeycombs versus screens to smooth the tunnel flow and a rapid tunnel dynamic pressure reducer are recommended to improve tunnel performance.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center High Reynolds Number Res. - 1980; p 153-161
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  • 25
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    Report of the wind tunnel/flight correlation panel (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Basic calibration of the tunnel prior to conducting any tests, the areas requiring wind tunnel/flight test correlation for validating the NTF, and recommendations for achieving validation of the NTF are discussed.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center High Reynolds Number Res. - 1980; p 249-262
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  • 26
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    High lift technology (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The NASA Langley high lift technology program is reviewed and elements of the program which are considered Reynolds number sensitive are discussed. The Energy Efficient Transport (EET) and Supersonic Cruise Research (SCR) models proposed for high lift studies in the National Transonic Facility (NTF) are described. Recommendations regarding the NTF facility and test techniques are presented.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 197-213
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  • 27
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    Wall interference effects: Status review (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The interference technology incorporated into the NTF design (hardware) and the emerging transonic wall interference assessment correction procedures (software) to be employed when the NTF becomes operational was reviewed. It is anticipated that the early experiments will provide data relevant to wall interference effects.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 123-241
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  • 28
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    Configuration aerodynamics (1981)
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    Publication Date: 2011-08-18
    Description: Static aerodynamic research related to aircraft configurations in their cruise or combat modes is discussed. Subsonic transport aircraft, transonic tactical aircraft, and slender wing aircraft are considered. The status and plans of Langley's NTF configuration research program are reviewed. Recommendations for near term configuration research are made.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 217-234
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  • 29
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    Comments on Reynolds number effects and the role of NTF in the development of air vehicles (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The National Transonic Facility (NTF) capability to match the full scale Reynolds numbers of all but the largest airplanes is discussed. Conversion factors to enable calculation of Sl-unit equivalents for all U.S. units are listed. Using data from several facilities, analytic methods, and flight test data, a competetive aircraft in the relatively low Reynolds number was developed. The NTF offers the capability to obtain data at full scale Reynolds numbers in the cruise condition for most of the products, and will be much closer than previous tunnels to full scale Reynolds number for the operating envelopes. It is primarily on the operating envelope that Reynolds number effects are most important and least predictable.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center High Reynolds Number Res. - 1980; p 143-148
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  • 30
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    Developing new architectures for the Block 2 VLBI correlator system (1981)
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    Publication Date: 2011-08-18
    Description: The overall LSI (large-scale integrated circuits) architecture design and current status of the VBLI (very long baseline interferometry) block 2 correlator is addressed. The VBLI correlator algorithms demand a computing system that provides a throughput of hundreds of millions of instructions per second to perform cross-correlation detection for six baselines. The LSI technology lights the way for the computation of complex parallel process and is raising the upper bound of computerization.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Progr. Rept. 42-64; p 30-40
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  • 31
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    A four-way distribution amplifier for reference signal distribution (1981)
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    Publication Date: 2011-08-18
    Description: A four way distribution amplifier with up to 100 dB isolation and with low phase noise of -140 dBc in a 1 Hz bandwidth 10 Hz from a 100 MHz signal was developed. It is to be used in the stabilized optical fiber distribution system to provide multiple outputs.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Telecommun. and Data Acquisition; p 31-34
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  • 32
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    Solution of the transonic full potential equation in conservative form using an implicit algorithm (1981)
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    Publication Date: 2011-08-18
    Description: The paper presents numerical solutions of the full potential equation in conservative form. The iteration scheme used is a fully implicit approximate factorization technique and provides a significant improvement in convergence speed relative to standard successive line overrelaxation algorithms. The spatial differencing algorithm is centrally differenced in both subsonic and supersonic regions to maintain stability. This effectively approximates rotated differencing, thereby greatly improving the reliability of the algorithm.
    Keywords: AERODYNAMICS
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  • 33
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    Computation of airfoil buffet boundaries (1981)
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    Publication Date: 2011-08-18
    Description: The ILLIAC IV computer has been programmed with an implicit, finite-difference code for solving the thin layer compressible Navier-Stokes equation. Results presented for the case of the buffet boundaries of a conventional and a supercritical airfoil section at high Reynolds numbers are found to be in agreement with experimentally determined buffet boundaries, especially at the higher freestream Mach numbers and lower lift coefficients where the onset of unsteady flows is associated with shock wave-induced boundary layer separation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Nov. 198
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    A prediction model for bipolar RAMs in a high energy ion/proton environment (1981)
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    Publication Date: 2011-08-18
    Description: A model has been developed which predicts the relative susceptibility of bipolar RAMs to heavy ion and proton upset. During the course of evaluating this model, physical and electrical variations were also evaluated indicating that the minimum internal signal level is the primary upset susceptibility indicator. Unfortunately, all of the physical and electrical variations expected during a normal product development cycle are in direct opposition to improved high-energy particle upset tolerance. Hence, a trade-off between highly susceptible, low power (medium speed) devices must be made against the less susceptible, higher power (high speed) equivalent device, taking into account the systems trade-off with respect to system power, software, error correction procedures and/or circuit redundancy.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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  • 35
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    An advanced, radiation hardened bulk CMOS/LSI technology (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An advanced, second generation, bulk, Si-gate CMOS process is described. This process is capable of producing LSI and VLSI parts that are latch-up free and hardened to total dose levels in excess of 2 x 10 to the 5th rad-Si for applications in space and weapons radiation environments. Two memories designed to use this process are also described. Both circuits are 4096-bit, static CMOS RAMs.
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  • 36
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    Investigation for single-event upset in MSI devices (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The reported investigation shows that low-power TTL, standard TTL, low-power Schottky, and Schottky devices are all subject to upset by heavy ions. Low-power Schottky was the most sensitive of the device technologies tested. No evidence was found to correlate sensitivity to cosmic rays with any particular device manufacturer. The probability of upset of the logic devices is comparable to that of RAM's on a per-flip-flop basis, based on RAM data obtained by Kolasinski et al. (1979). The testing was performed by subjecting the devices to 120 MeV krypton ions from a cyclotron.
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  • 37
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    Activation energies of thermal annealing of radiation-induced damage in n- and p-channels of CMOS integrated circuits. II (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The procedures described by Danchenko et al. (1980) are applied to devices of RCA's Z-process (100,000 rad-hard). A thermal annealing investigation of the Z-process reveals an annealing behavior of the p-channels that is anomalous when compared with the p-channels of the commercial and J-processes. It is noted that the thermal annealing-induced shift of the threshold potential extends far below the original value; this necessitated the development of a new mathematical treatment, the treatment presented in the paper.
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  • 38
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    CMOS RAM cosmic-ray-induced-error-rate analysis (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A significant number of spacecraft operational anomalies are believed to be associated with cosmic-ray-induced soft errors in the LSI memories. Test programs using a cyclotron to simulate cosmic rays have established conclusively that many common commercial memory types are vulnerable to heavy-ion upset. A description is given of the methodology and the results of a detailed analysis for predicting the bit-error rate in an assumed space environment for CMOS memory devices. Results are presented for three types of commercially available CMOS 1,024-bit RAMs. It was found that the HM6508 is susceptible to single-ion induced latchup from argon and krypton ions. The HS6508 and HS6508RH and the CDP1821 apparently are not susceptible to single-ion induced latchup.
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  • 39
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    Annual Conference on Nuclear and Space Radiation Effects, 18th, University of Washington, Seattle, WA, July 21-24, 1981, Proceedings (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Single event upset phenomena are discussed, taking into account cosmic ray induced errors in IIL microprocessors and logic devices, single event upsets in NMOS microprocessors, a prediction model for bipolar RAMs in a high energy ion/proton environment, the search for neutron-induced hard errors in VLSI structures, soft errors due to protons in the radiation belt, and the use of an ion microbeam to study single event upsets in microcircuits. Basic mechanisms in materials and devices are examined, giving attention to gamma induced noise in CCD's, the annealing of MOS capacitors, an analysis of photobleaching techniques for the radiation hardening of fiber optic data links, a hardened field insulator, the simulation of radiation damage in solids, and the manufacturing of radiation resistant optical fibers. Energy deposition and dosimetry is considered along with SGEMP/IEMP, radiation effects in devices, space radiation effects and spacecraft charging, EMP/SREMP, and aspects of fabrication, testing, and hardness assurance.
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  • 40
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    Experimental verification of a computational procedure for the design of TWT-refocuser-MDC systems (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A comparison of analytical and experimental results is presented for a high performance dual-mode helix TWT, equipped with multistage depressed collectors (MDC), and operated over conditions ranging from saturation to the linear regime. The computations are carried out with advanced multidimensional computer programs which model the electron beam as a series of disks or rings of charge and follow their trajectories from the RF input of the TWT, through the slow-wave structure, through the refocusing system, to their points of impact in the depressed collector. TWT performance, collector efficiency, and collector current distribution are computed and compared with measurements. Very good agreement is obtained between computed and measured TWT performance and collector efficiencies. The analytical techniques were subsequently applied to the design of a smaller MDC of nearly equal efficiency.
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  • 41
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    Fabrication of a 16-channel integrated optical data preprocessor (1981)
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    Publication Date: 2011-08-18
    Description: A 16-channel integrated optical data preprocessor based on a Mach-Zehnder interferometer configuration has been fabricated on a LiNbO3 substrate. The fabrication procedure is reviewed and a detailed discussion of the steps utilized to integrate the individual components is presented. The results of the device testing experiments are also discussed.
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  • 42
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    Application of unsteady airfoil theory to rotary wings (1981)
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    Publication Date: 2011-08-18
    Description: A clarification is presented on recent work concerning the application of unsteady airfoil theory to rotary wings. The application of this theory may be seen as consisting of four steps: (1) the selection of an appropriate unsteady airfoil theory; (2) the resolution of that velocity which is the resultant of aerodynamic and dynamic velocities at a point on the elastic axis into radial, tangential and perpendicular components, and the angular velocity of a blade section about the deformed axis; (3) the expression of lift and pitching moments in terms of the three components; and (4) the derivation of explicit expressions for the components in terms of flight velocity, induced flow, rotor rotational speed, blade motion variables, etc.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 18; July 198
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  • 43
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    The coupling between flow instabilities and incident disturbances at a leading edge (1981)
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    Publication Date: 2011-08-18
    Description: It is now generally agreed that an external disturbance field, such as an incident acoustic wave, can effectively couple to instabilities of a flow past a trailing edge. One purpose of the present paper is to show that there are situations where a similar coupling can occur at a leading edge. The process is analyzed and the effects of experimentally controllable parameters are assessed. It is important to account for such phenomena when evaluating the effect of external disturbances on transition.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 104; Mar. 198
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  • 44
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    A discrete vortex method for the non-steady separated flow over an airfoil (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A discrete vortex method was used to analyze the separated non-steady flow about a cambered airfoil. The foil flow modelling is based on the thin lifting-surface approach, where the chordwise location of the separation point is assumed to be known from experiments or flow-visualization data. Calculated results provided good agreement when compared with the post-stall aerodynamic data of two airfoils. Those airfoil sections differed in the extent of travel of the separation point with increasing angle of attack. Furthermore, the periodic wake shedding was analyzed and its time-dependent influence on the airfoil was investigated.
    Keywords: AERODYNAMICS
    Type: Journal of Fluid Mechanics; 102; Jan. 198
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  • 45
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    Pathfinder model program for the National Transonic Facility (1981)
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    Publication Date: 2011-08-18
    Description: An overview of the Pathfinder Models Program is presented. The Pathfinder program is a major research and development activity in support of the National Transonic Facility Activation Plan. The program scope, models design approach, and Pathfinder model configurations are presented along with a discussion of major supportive program activities. The anticipated design criteria for NTF models are presented.
    Keywords: AERODYNAMICS
    Type: High Reynolds Number Res. - 1980; p 37-52
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  • 46
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    Electrical load management at the Goldstone DSN Complex (1981)
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    Publication Date: 2011-08-18
    Description: A Power Load Management Plan was deveoped which utilizes the unique power generating capabilities of the stations to reduce the stress on the local utility's reserve capacity and reduce the cost of electrical power at the stations. The plan has greatly reduced the cost of Goldstone electrical power by completely eliminating the use of commercial power during the local utility's high usage periods each day.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 219-225
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  • 47
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    Improved cooling design for high power waveguide system (1981)
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    Publication Date: 2011-08-18
    Description: Testing of X band high power components in a traveling wave resonator indicates that this improved cooling design reduces temperature in the waveguide and flange. The waveguide power handling capability and power transmission reliability is increased substantially.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 104-107
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  • 48
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    High-power transmitter automation, part 2 (1981)
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    Publication Date: 2011-08-18
    Description: The current status of the transmitter automation development is reported. The work described is applicable to all transmitters in the Deep Space Network. New interface and software designs are described which improve reliability and reduce the time required for subsystem turn on and klystron saturation.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 114-117
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  • 49
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    An evaluation of the Intel 2920 digital signal processing integrated circuit (1981)
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    Publication Date: 2011-08-18
    Description: The circuit consists of a digital to analog converter, accumulator, read write memory and UV erasable read only memory. The circuit can convert an analog signal to a digital representation, perform mathematical operations on the digital signal and subsequently convert the digital signal to an analog output. Development software tailored for programming the 2920 is presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Telecommun. and Data Acquisition Rept.; p 108-113
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  • 50
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    Trailing edge noise prediction using Amiet's method (1981)
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    Publication Date: 2011-08-18
    Description: Amiet's (1976, 1978) solution to the problem of airfoil trailing edge noise prediction is discussed in light of the results of evanescent wave theory's application to the measured surface pressure behavior near the trailing edge of an airfoil with a turbulent boundary layer. The method employed by Amiet has the advantage of incorporating the effect of finite chord in its solution. The assumed form of the pressure distribution is examined as well as the constant turbulent boundary layer convection assumption, which is found to be unnecessarily restrictive.
    Keywords: AERODYNAMICS
    Type: Journal of Sound and Vibration; 77; Aug. 8
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  • 51
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    Forebody drag reduction (1981)
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    Publication Date: 2011-08-18
    Description: It is shown that the mechanisms of forebody drag reduction by means of either a spike or a forward-facing jet are similar, with the maximum achievable drag reduction being of the same order. Because the jet may be a relatively cool gas, however, the forward facing jet has the additional capability of reducing the aerodynamic heating that is so severe at high Mach numbers. By means of the correlation presented, jet ejection parameters may be chosen to achieve maximum permissible forebody drag reduction. The correlation method uses a momentum coefficient that characterizes jet efflux and freestream conditions.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Oct. 198
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  • 52
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    Unsteady Newton-Busemann flow theory. II - Bodies of revolution (1981)
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    Publication Date: 2011-08-18
    Description: A complete Newtonian flow theory is presented for unsteady flow past oscillating bodies of revolution of general shape at very high Mach numbers, consideration being given to a centrifugal force correction to the impact pressures. Expressions are obtained for the unsteady pressure and the stability derivatives are presented in closed form. It is stressed that the correction for the centrifugal force, which arises because of the curved trajectories that fluid particles follow along the surface subsequent to their impact, must not be neglected. If the correction is included, the theory is shown to be in excellent agreement with experimental results for relatively sharp cones. Theoretical results are in poor agreement with experimental results in air for bodies having moderate or large-nose bluntness.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 19; Oct. 198
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  • 53
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    Super-Schottky mixer performance at 92 GHz (1981)
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    Publication Date: 2011-08-18
    Description: As part of a program to investigate the behavior of superconducting Schottky mixers at high frequencies, the mixing and video performance of several super-Schottky diodes (a 3-micron active diameter, and a doping concentration of 2 x 10 to the 19th per cu cm) have been tested at 92 GHz. At 92 GHz, video responsivities were typically 80 A/W (corrected for RF mismatch). Conversion loss (corrected for both RF and IF mismatches) was typically not less than 18 dB. As expected, diode temperature was low (less than 5 K). Video responsivity and conversion loss were also measured at an RF frequency of 3.95 GHz. These data were used with the measured volt-ampere characteristics of the diodes to compare theoretical predictions of diode performance at 92 GHz, in both the video and mixing modes, with the high-frequency data
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: IEEE Transactions on Microwave Theory and Techniques; MTT-29; Aug. 198
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  • 54
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    Traveling-wave tube efficiency improvement with textured pyrolytic graphite multistage depressed collector electrodes (1981)
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    Publication Date: 2011-08-18
    Description: The improved efficiency of a multistage depressed collector (MDC) with ion-beam textured pyrolytic graphite electrode surfaces is demonstrated by comparison with the performance of other MDC's tested with the same microwave RF amplifier traveling-wave tube (TWT). Because of the sensitivity of overall TWT efficiency to collector efficiency, significant improvements in TWT performance are possible with the use of textured pyrolytic graphite MDC's.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: IEEE Electron Device Letters; EDL-2; Oct. 198
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  • 55
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    Cosmic ray induced errors in I2L microprocessors and logic devices (1981)
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    Publication Date: 2011-08-18
    Description: Large-scale integrated (LSI) devices fabricated with integrated injection logic (I2L) were studied by both heavy ion experiments and device analysis to determine the upset threshold, the charge collection volumes and ultimately the probability for upset in the galactic cosmic ray spectrum. The devices studied, the SEP9900A, the SBP9989 and the P-Code generator were fabricated by Texas Instruments, Inc.
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  • 56
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    High temperature (Al2O3) insulation and light weight conductors (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The of an aluminum conductor with an aluminum oxide insulation film was investigated. Aluminum oxide insulated wire or strip (with a melting point of 2050 C) is unique for applications in the electronic, missile, atomic reactor, aerospace, and aircraft industries. The oxide film is highly flexible, suitable for all windings of any size and shape of coil (magnetic). Briefly touched upon are the ultraviolet, proton gamma radiation uses, as well as high vacuum and cryogenic applications. Since the film is inorganic and chemically inert, it does not age or deteriorate in storage and has good dielectric properties (1000 volts per mil).
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 123-219
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  • 57
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    A presently available energy supply for high temperature environment (550-1000 deg F) (1981)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Sodium-sulfur cells attractive electric energy storage device for long service, are discussed. The state of art is given. More than 200 Wh/kg cells were tested. The known range of working temperature is 550 to 750 F. Self-discharge is quite nonexistent for months in operation. The technical basis for expecting an operating range up to 1,000 F under a high pressure atmosphere is given. Possibilities to adapt size and characteristics to particular interplanetary missions are discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 107-109
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  • 58
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    Stuffed MO layer as a diffusion barrier in metallizations for high temperature electronics (1981)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Auger electron spectroscopy was employed to characterize the diffusion barrier properties of molybdenum in the CrSi2/Mo/Au metallization system. The barrier action of Mo was demonstrated to persist even after 2000 hours annealing time at 300 C in a nitrogen ambient. At 340 C annealing temperature, however, rapid interdiffusion was observed to have occurred between the various metal layers after only 261 hours. The presence of controlled amounts of oxygen in the Mo layer is believed to be responsible for suppressing the short circuit interdiffusion between the thin film layers. Above 340 C, its is believed that the increase in the oxygen mobility led to deterioration of its stuffing action, resulting in the rapid interdiffusion of the thin film layers along grain boundaries.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 111-114
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  • 59
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    Solid state microelectronics tolerant to radiation and high temperature (1981)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: The 300 C electronics technology based on JFET thick film hybrids was tested up to 10 to the 9th power rad gamma (Si) and 10 to the 15th power neutrons/sq cm. Circuits and individual components from this technology all survived this total dose although some devices required 1 hour of annealing at 200 or 300 C to regain functionality. This technology used with real time annealing should function to levels greater than 10 to the 10th power rad gamma and 10 to the 16th power n/sq cm.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 93-96
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  • 60
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    Hybrid A/D converter for 200 deg C operation (1981)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: A 12 bit A/D converter was designed and developed which will operate at 200 C with .05 linearity, 1/accuracy, 350 WSec conversion time, and only 455 mW power consumption. This product also necessitated the development of a unique three metal system in which aluminum wire bonding is done utilizing aluminum bonding pads, gold wire bonding to all gold areas, and employment of a nickel interface between gold and aluminum connections. This system totally eliminates the formation of a intermetallics at the bonding interface which can lead to bond failure. This product represents an advancement in electronics as it proved the operation of integrated circuits at high temperature, as well as providing information about both the electrical and mechanical reliability of hybrid circuits at 200 C.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 85-88
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  • 61
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    Minus 55 to plus 200 deg C 12 bit analog-to-digital converter (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A 12 bit successive approximation analog to digital converter that offers moderately high speed precision data conversion at a reasonable level of cost and complexity is studied. The ADCH10HT extends this capability over a temperature range of -55 to +200 C. No missing-code performance is maintained over the entire temperature range. The converter is completely self-contained with internal clock and +10 volt reference. The CMOS devices offer low power dissipation, so that the internal temperature of the hybrid circuit does not rise as much from self heating. In CMOS circuits, pn junction leakage currents are returned to the supplies so that the logic keeps working at temperatures up to 250 C.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 77-79
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  • 62
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    Process characteristics and design methods for a 300 deg quad OP amp (1981)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: The results of process characterization, circuit design, and reliability studies for the development of a quad OP amplifier intended for use up to 300 C are presented. A dielectrically isolated complementary vertical bipolar process was chosen to fabricate the amplifier in order to eliminate isolation leakage and the possibility of latch up. Characterization of NPN and PNP junctions showed them to be suitable for use up to 300 C. Interconnect reliability was predicted to be greater than four years mean time between failure. Parasitic MOS formation was eliminated by isolation of each device.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 81-84
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    Electrical switching in cadmium boracite single crystals (1981)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Cadmium boracite single crystals at high temperatures ( 300 C) were found to exhibit a reversible electric field-induced transition between a highly insulative and a conductive state. The switching threshold is smaller than a few volts for an electrode spacing of a few tenth of a millimeter corresponding to an electric field of 100 to 1000 V/cm. This is much smaller than the dielectric break-down field for an insulator such as boracite. The insulative state reappears after voltage removal. A pulse technique revealed two different types of switching. Unstable switching occurs when the pulse voltage slightly exceeds the switching threshold and is characterized by a pre-switching delay and also a residual current after voltage pulse removal. A stable type of switching occurs when the voltage becomes sufficiently high. Possible device applications of this switching phenomenon are discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 67-70
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  • 64
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    Whatever happened to silicon carbide (1981)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: The progress made in silicon carbide semiconductor devices in the 1955 to 1975 time frame is examined and reasons are given for the present lack of interest in the material. Its physical and chemical properties and methods of preparation are discussed. Fabrication techniques and the characteristics of silicon carbide devices are reviewed. It is concluded that a combination of economic factors and the lack of progress in fabrication techniques leaves no viable market for SiC devices in the near future.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 71-76
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  • 65
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    Development of integrated thermionic circuits for high-temperature applications (1981)
    In:  CASI
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    Publication Date: 2017-10-02
    Description: Integrated thermionic circuits (ITC) capable of extended operation in ambient temperatures up to 500 C are studied. A set of practical design and performance equations is demonstrated. Experimental results are discussed in which both devices and simple circuits were successfully operated in 5000 C environments for extended periods. It is suggested that ITC's may become an important technology for high temperature instrumentation and control systems in geothermal and other high temperature environments.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 49-53
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    Amorphous metallizations for high-temperature semiconductor device applications (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The initial results of work on a class of semiconductor metallizations which appear to hold promise as primary metallizations and diffusion barriers for high temperature device applications are presented. These metallizations consist of sputter-deposited films of high T sub g amorphous-metal alloys which (primarily because of the absence of grain boundaries) exhibit exceptionally good corrosion-resistance and low diffusion coefficients. Amorphous films of the alloys Ni-Nb, Ni-Mo, W-Si, and Mo-Si were deposited on Si, GaAs, GaP, and various insulating substrates. The films adhere extremely well to the substrates and remain amorphous during thermal cycling to at least 500 C. Rutherford backscattering and Auger electron spectroscopy measurements indicate atomic diffussivities in the 10 to the -19th power sq cm/S range at 450 C.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 35-37
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    Ohmic contacts to GaAs for high-temperature device applications (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Ohmic contacts to n-type GaAs were developed for high temperature device applications up to 300 C. Refractory metallizations were used with epitaxial Ge layers to form the contacts: TiW/Ge/GaAs, Ta/Ge/GaAs, Mo/Ge/GaAs, and Ni/Ge/GaAs. Contacts with high dose Si or Se ion implantation of the Ge/GaAs interface were also investigated. The contacts were fabricated on epitaxial GaAs layer grown on N+ or semi-insulating GaAs substrates. Ohmic contact was formed by both thermal annealing (at temperatures up to 700 C) and laser annealing (pulsed Ruby). Examination of the Ge/GaAs interface revealed Ge migration into GaAs to form an N+ doping layer. The specific contact resistances of specimens annealed by both methods are given.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 39-42
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    Assessment of high temperature metallizations for I(2)L and CMOS technologies (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: High temperature barrier metallizations were assessed and tested for I(2)L and CMOS applications. Life tests were accelerated to 375 C in view of the -55 C to +300 C temperature range established for engine-located electronics without fuel cooling. The gold-refractory metallizations evaluated were Au-TiW-PtSi, Au-TiW/TiO2/TiW-PtSi and Au-TiW(N)-PtSi. These metallization systems were thermally annealed to at least 375 C for up to 250 hours. The critical requirement for stable diffusion barrier is the TiW grain size. Small grain (250A-500A) films were observed to be stable up to 375 C. Deposition to TiW diffusion barrier in the presence of oxygen and nitrogen also results in an effective diffusion barrier. Auger electron spectroscopy profiles of the PtSi indicates some penetration by the TiW. In the case of PtSi/TiW interface, the redistribution of oxygen further passivates the system by forming a TiO2 layer at the interface.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 33-34
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    Passive components for high temperature operation (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The development of resistors, capacitors, and interconnect metalizations utilizing a low pressure chemical vapor deposition (LPCVD) process is described. The LPCVD process allows the passive components to be fabricated at temperatures higher than their highest operating temperatures. The deposition of thin films by LPCVD is accomplished by reacting one or more gases on the surface of a heated substrate. The substrates to be coated are placed on a graphite susceptor and then loaded into the center of a quartz reaction tube. The RF power is applied to the coil on the outside of the reaction tube which in turn is coupled into the graphite susceptor causing it to heat. Pressures of several torr or less are typical, with carrier flow rates of 0.1 to 2.0 liters/min. Nitrogen, hydrogen, and helium are typical carrier gases. These are controlled with mass flow controllers and the pressure is continuously monitored with a capacitive manometer. Materials selection and device testing are also discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Lewis Research Center Proc. of the Conf. on High-Temp. Electron.; p 21-23
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    Top-mounted inlet system feasibility for transonic-subsonic fighter aircraft applications (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: To inlet flow field and engine inlet performance data for an advanced fighter aircraft configuration were obtained over the Mach 0.6 to 2.0 range. The studies not only provided extensive data for the baseline arrangement, but also evaluated the effects of key aircraft configuration variables (inlet location, canopy-dorsal integration, wing leading-edge extension planform area, and variable incidence canards) on top inlet performance. In order to set these data in the context of practical aircraft systems top inlet performance is compared with that of more conventional inlet/airframe integrations. The results of these evaluations show that, for the top inlet configuration tested, relatively good inlet performance and compatibility characteristics are maintained during subsonic and transonic maneuver. However, at supersonic speeds, flow expansion over the forebody and wings causes an increase in local inlet Mach number subsequently reduces inlet performance levels. These characteristics infer that although top inlets many not pose a viable design option for aircraft requiring a high degree of supersonic maneuverability, they have distinct promise for vehicles with subsonic and transonic maneuver capabilities.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. of Power Plant Installation; 17 p
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  • 71
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    Impact of high-alpha aerodynamics on dynamic stability parameters of aircraft and missiles (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The aerodynamic phenomena associated with high angles of attack and their effects on the dynamic stability characteristics of airplane and missile configurations are examined. Information on dynamic effects is limited. Steady flow phenomena and their effects on the forces and moments are reviewed. The effects of asymmetric vortices and of vortex bursting on the dynamic response of flight vehicles are reviewed with respect to their influence on: (1) nonlinearity of aerodynamic coefficients with attitude, rates, and accelerations; (2) cross coupling between longitudinal and lateral directional models of motion; (3) time dependence and hysteresis effects; (4) configuration dependencey; and (5) mathematical modeling of the aerodynamics.
    Keywords: AERODYNAMICS
    Type: AGARD Dyn. Stability Parameters; 18 p
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  • 72
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    An assessment of theoretical models for viscous and transonic flow (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Topics discussed include shear flow models, simplified models for treating separation, classical linear theory, a local linearization theory, a transonic linear theory, a transonic nonlinear theory, the experiment of Davis, and the experiment of Tijdeman. It is concluded that shear flow models, which have proven very accurate in taking into account boundary layer effects for panel flutter, are likely to be less so for lifting surface flutter. For many applications in transonic flow, transonic linear theory will be adequate.
    Keywords: AERODYNAMICS
    Type: AGARD Boundary Layer Effects on Unsteady Airloads; 28 p
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    Experimental studies of scale effects on oscillating airfoils at transonic speeds (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Scale effects are discussed with reference to a conventional airfoil (NACA 64A010) and a supercritical airfoil (NLR 7301) at mean flow conditions that support both weak and strong shock waves. During the experiment the Reynolds number was varied from 3 x 10 to the sixth power at time history data are presented over the range of reduced frequencies that are important in aeroelastic applications. The experimental data show that viscous effects are important in the case of the supercritical airfoil at all flow conditions and in the case of the conventional airfoil under strong shock wave conditions. Some frequency dependent viscous effects were also observed.
    Keywords: AERODYNAMICS
    Type: AGARD Boundary Layer Effects on Unsteady Airfoils; 13 p
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  • 74
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    Natural laminar flow data from full-scale flight and wind-tunnel experiments (1981)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: Experimental results obtained at NASA Langley during studies of natural laminar flow (NLF) over commercially produced aircraft surfaces are reported. The general aviation aircraft examined were light aircraft, yet displayed NLF extents close to the maximum available and equivalent to high performance business aircraft flying envelopes. Sublimating chemicals and acoustic detection techniques were employed to measure the boundary layer transition. Theoretical predictions of boundary layer stability were found to match well with the experimental data, with consideration given to both swept wings and the amplitudes of allowable waves on the airfoil surfaces. The presence of the NLF on the airfoil surfaces confirmed the benefits available from use of composite materials for airfoil surfaces.
    Keywords: AERODYNAMICS
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    Corrosion in NiCd cells (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Corrosion in the terminals of nickel cadmium cells was investigated. Corrosion, crevice type corrosion, at the interface between the stainless steel material, the nickel material, and the braze was examined. It was concluded that in the welded areas there was no problem. There was corrosion of the crevice type in the brazed areas and some pitting was evident between the braze and the base material.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1981 GSFC Battery Workshop; p 415-420
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    A cause of the non-solderability of ceramic capacitor terminations (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The results of an analysis into the cause of the non-solderability of multiple defective part lots from two capacitor manufacturers are described. This analysis consisted of visual, scanning electron microscopic, surface, and metalographic examinations and analyses. The results indicated that non-solderability results from areas of excess porosity in the termination which are caused by segregation of ink constituents during manufacturing. This segregation can be minimized by proper monitoring and control of process variables; where excess porosity does occur, solderability can be improved by proper precleaning of parts.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 99-104
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  • 77
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    Specifying capacitors for performance and reliability in switching power supplies (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The three most commonly used switching circuits are the full bridge converter, the half bridge converter, and the forward converter. All three circuits use the same pulse width concept for regulation with the major difference being how many transistors are used for power handling. The full bridge uses four transistors, the half bridge uses two, and the forward converter uses one. In practical design, forward converters are used at 300 watts and below, half bridges at 300 to 600 watts, and full bridges above 600 watts. Regulation is achieved by alternately saturating diagonal pairs of transistors in the full bridge, alternately saturating transistors in the half bridge, and simply pulse modulating one transistor in the forward converter.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 69-73
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  • 78
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    Polyvinylidene fluoride film as a capacitor dielectric (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Thin strips of polyvinylidene fluoride film (PVDF) with vacuum deposited electrodes were made into capacitors by conventional winding and fabrication techniques. These devices were used to identify and evaluate the performance characteristics offered by the PVDF in metallized film capacitors. Variations in capacitor parameters with temperature and frequence were evaluated and compared with other dielectric films. Their impact on capacitor applications is discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 7-12
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    Natural Laminar Flow Flight Experiment (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A supercritical airfoil section was designed with favorable pressure gradients on both the upper and lower surfaces. Wind tunnel tests were conducted in the Langley 8 Foot Transonic Pressure Tunnel. The outer wing panels of the F-111 TACT airplane were modified to incorporate partial span test gloves having the natural laminar, flow profile. Instrumentation was installed to provide surface pressure data as well as to determine transition location and boundary layer characteristics. The flight experiment encompassed 19 flights conducted with and without transition fixed at several locations for wing leading edge sweep angles which varied from 10 to 26 at Mach numbers from 0.80 to 0.85 and altitudes of 7620 meters and 9144 meters. Preliminary results indicate that a large portion of the test chord experienced laminar flow.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Advan. Aerodyn. and Active Controls; p 135-144
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    Aerodynamic drag reduction tests on a box-shaped vehicle (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The intent of the present experiment is to define a near optimum value of drag coefficient for a high volume type of vehicle through the use of a boattail, on a vehicle already having rounded front corners and an underbody seal, or fairing. The results of these tests will constitute a baseline for later follow-on studies to evaluate candidate methods of obtaining afterbody drag coefficients approaching the boattail values, but without resorting to such impractical afterbody extensions. The current modifications to the box-shaped vehicle consisted of a full and truncated boattail in conjunction with the faired and sealed underbody. Drag results from these configurations are compared with corresponding wind tunnel results of a 1/10 scale model. Test velocities ranged up to 96.6 km/h (60 mph) and the corresponding Reynolds numbers ranged up to 1.3 x 10 to the 7th power based on the vehicles length which includes the boattail. A simple coast-down technique was used to define drag.
    Keywords: AERODYNAMICS
    Type: NASA-CR-176982 , NAS 1.26:176982
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  • 81
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    Why use case studies rather than simulation-gaming techniques or library research? (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Method which present a student with a more challenging and true to life situation of needing to conduct research in a problem solving context--and not thinking about organization of format until research and thinking are complete are investigated. Simulation-gaming techniques which attempt to teach initiative and creativity that library research are used for this purpose. However, it is shown case studies provide the greatest opportunities to engage the students in problem solving situations in which they develop skills as researchers and writers.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Research Center Tech. Commun., Pt. 1; p 99-103
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  • 82
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    High-frequency measurements of multilayer ceramic capacitors (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: A resonant coaxial transmission line, short circuited at one end and open circuited at the other, whose fundamental resonant frequency and Q factor are known, is perturbed with a test capacitor connected either in series at the shorted end of the line, or in shunt at the open end. Measuring the Q factor of the system with the delta f technique yields the effective series resistance, capacitance, and the Q factor of the test specimen. This method of measurement has the advantage that there are no adjustable elements to alter circuit conditions in an unprescribed way, the only variable is the frequency which can be measured with an uncertainty of less than 1 ppm, the loss of the line as a function of frequency is quite predictable, and the Q factor of the line can be made sufficiently high to support accurate measurements of low loss capacitors.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 119-122
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  • 83
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    Breakdown voltage of discrete capacitors under single-pulse conditions (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: For electrostatic capacitors the breakdown voltage is inherently related to the properties of the dielectric, with the important parameters being the dielectric field strength which is related to the dielectric constant and the dielectric thickness. These are not necessarily related to the capacitance value and the rated voltage, but generally the larger values of capacitance have lower breakdown voltages. Foil and wet slug electrolytics can withstand conduction currents pulses without apparent damage (in either direction for foil types). For solid tantalums, damage occurs whenever the capacitor charges to the forming voltage.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 53-62
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  • 84
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    Unstable insulation resistance in ceramic capacitors (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The effects of low and varying values of insulation resistance (IR) and their significance in the cause of failure in ceramic capacitors were investigated. Two specific instances involving hardware failure involving ceramic capacitors were examined. It is shown that monolithic, multilayer ceramic capacitors may exhibit low and unstable IR at low voltages, or exhibit no voltage. Other significant results are reported.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Capacitor Technol., Appl. and Reliability; p 27-31
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    Radiation response and electrical properties of polymer energy storage capacitors: PVF2, Polysulfone, and Mylar (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Efforts were made to develop a polymer film capacitor that is tolerant to radiation. The capacitors are to be utilized in a high voltage pulse discharge application. Radiation response data at high dose/dose rate levels are presented for polyvinylidene fluoride (PVF2), polysulfone, and Mylar. The results show that PVF2 is the most radiation tolerant while Mylar is the least tolerant. The data also show that the radiation response is quite dependent on operating electric stress.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 1-5
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  • 86
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    The phenomenon of dynamic stall (1981)
    In:  Other Sources
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    Publication Date: 2019-01-25
    Description: Dynamic stall and its consequences which are important to aircraft design and operation are discussed. A certain degree of unsteadyness always accompanies the flow over streamlined bodies at high angle of attack, however, the stall of lifting surface undergoing unsteady motion is more complex than static stall. Dynamic stall remains a major unsolved problem with a variety of applications in aeronautics, hydrodynamics and wind engineering.
    Keywords: AERODYNAMICS
    Type: Von Karman Inst. for Fluid Dynamics Unsteady Airloads and Aeroelastic Probl. in Separated and Transonic Flow; 28 p
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  • 87
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    Development of a sub-miniature rubidium oscillator for SEEKTALK application (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Warm-up and size challenges to oscillator construction are presented as well as the problems involved in these tasks. The performance of M-100 military rubidium oscillator is compared to that of a subminiture rubididum oscillator (M-1000). Methods of achieving 1.5 minute warm-up are discussed as well as improvements in performance under adverse environmental conditions, including temperature, vibration, and magnetics. An attempt is made to construct an oscillator error budget under a set of arbitrary mission conditions.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center Proc. of the 12th Ann. Precise Time and Time Interval Appl. and Planning Meeting; p 719-742
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  • 88
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    Frequency and time generation and control (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: High precision quartz crystal oscillators, cesium beam atomic resonators, and cesium beam atomic standards for time and frequency generation equipment for ground, airborne, and space use are described. Because of the high risk factors involved, and the commercial applications of these products being too far off in the future, private capital for research and development is difficult if not impossible to obtain. More specific analysis and recommendations to overcome these difficulties are objectively presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center Proc. of the 12th Ann. Precise Time and Time Interval Appl. and Planning Meeting; p 211-251
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  • 89
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    Capacitor DPA: Does it do any good? (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Methods of destructive physical analysis (DPA) are suggested which might have more usefulness if the procedures followed lines of accelerated testing. A brief presentation of DPA procedures is followed by a discussion of their value.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 125-129
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  • 90
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    A comparison of screening techniques for ceramic capacitors (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The techniques involved are ultrasonic scanning, neutron radiography, scanning laser acoustic microscopy, and voltage conditioning. The test capacitor, for this first phase, is a 0.47 uF, 50V capacitor style CKR06. Eighteen of 768 devices failed in voltage conditioning with elapsed times from 15 minutes to 1239 hours. Eleven of the failures were detected by ultrasonic scanning. Four failures were found by neutron radiography. Fourteen failures showed up in the acoustic microscopy test. Three failures in voltage conditioning were not detected by any of the techniques. Failures were confirmed by destructive physical analysis. There is no direct relationship between the size of the defect and electrical failure.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 111-117
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  • 91
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    Monolithic ceramic capacitors for high reliability applications (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Monolithic multi-layer ceramic dielectric capacitors are widely used in high reliability applications in spacecraft, launch vehicles, and military equipment. Their relatively low cost, wide range of values, and package styles are attractive features that result in high usage in electronic circuitry in these applications. Design and construction of monolithic ceramic dielectric capacitors, defects that can lead to failure, and methods for defect detection that are being incorporated in military specifications are discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 75-88
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  • 92
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    Failure analysis methods for capacitors (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The basic steps in the failure analysis of discrete capacitors used in electronic circuit boards and hybrid assemblies are described. These steps include: visual examination; functional test; disassembly; isolation of the failure site; and documentation.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 131-148
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  • 93
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    Ultrasonic scanning of multilayer ceramic chip capacitors (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: Ultrasonic scanning is compared to neutron radiography and scanning laser acoustic microscopy (SLAM). Data show that SLAM and ultrasonic scanning evaluations are in good agreement. There is poor agreement between N-ray and both ultrasonic techniques because N-ray is insensitive to all but the grossest delaminations. Statistical analysis show a good correlation between ultrasonic scanning and destructive physical analysis.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Technol., Appl. and Reliability; p 105-110
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  • 94
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    Accelerated life testing and reliability of high K multilayer ceramic capacitors (1981)
    In:  Other Sources
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    Publication Date: 2016-06-07
    Description: The reliability of one lot of high K multilayer ceramic capacitors was evaluated using accelerated life testing. The degradation in insulation resistance was characterized as a function of voltage and temperature. The times to failure at a voltage-temperature stress conformed to a lognormal distribution with a standard deviation approximately 0.5.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 93-97
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  • 95
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    Capacitors, thermal rating/derating (ac-dc operation) (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Application techniques for determining performance and ratings of cased capacitors under combined operation as a function of the actual operating conditions are described. Thermal impedances between the case and external environment and between the internal hot spot and case are taken into account.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 89-97
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    Internal fuse modules for solid tantalum capacitors (1981)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Miniature fuse modules were designed for and incorporated into two styles of solid tantalum capacitors. One is an epoxy molded, radial leaded, high frequency decoupling capacitor; the other is an hermetically sealed device with axial lead wires. The fusible element for both devices consists of a fine bimetallic wire which reacts exothermically upon reaching a critical temperature and then disintegrates. The desirability of having fused devices is discussed and design constraints, in particular those which minimize inductance and series resistance while optimizing fuse actuation characteristics, are reviewed. Factors affecting the amount of energy required to actuate the fuse and reliability of acuation are identified.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 63-68
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  • 97
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    Super miniaturization of film capacitor dielectrics (1981)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The alignment of the stable electrical characteristics of film capacitors in the physical dimensions of ceramic and tantalum capacitors are discussed. The reliability of polycarbonate and mylar capacitors are described with respect to their compatibility with military specifications. Graphic illustrations are presented which show electrical and physical comparisons of film, ceramic, and tantalum capacitors. The major focus is on volumetric efficiency, weight reduction, and electrical stability.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 39-43
    Format: text
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  • 98
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    Performance comparison: Aluminum electrolytic and solid tantalum capacitor (1981)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: Several key electrical and environmental parameters of latest technology aluminum electrolytic and solid tantalum capacitors were evaluated in terms of price fluctuations of tantalum metal. Performance differences between solid tantalums and aluminum electrolytics are examined.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 19-25
    Format: text
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  • 99
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    Effects of severe stressing on tantalum capacitors (1981)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The ultimate capabilities of an all tantalum capacitor were determined and evaluated. The evaluation included: 175 C life; 100 cycle thermal shock; 70 g random vibration; 3000 g shock; and 90 C ase ripple current.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 45-52
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  • 100
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    Influence of current needs on the advancement of aluminum electrolytic capacitors (1981)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The need for cost effective, high performance, long life capacitors with improved reliability is discussed. It is shown that a low cost, miniature aluminum capacitor, with improved reliability and proven life, can be produced with existing technology. It is further shown that the capacitor can be specified for 125 C life and shelf test requirements, and meet established standards for their parametric performance.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Capacitor Technol., Appl. and Reliability; p 33-37
    Format: text
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    NASA TECHNICAL REPORTS
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