On the trapping level disposition in cadmium sulfide.
Electron trapping level disposition in CdS energy band gap indicating single energy scheme
Faeth, P. A.↗
SEARCH · Engineering Papers
Results for “Band gap”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
The preparation and properties of vapor- deposited single-crystalline GaN
Vapor deposited GaN single crystals tested for electrical and optical properties, determining band gap energy, electron concentration, etc
Maruska, H. P.↗
Development of aluminum alloy compounds for electroluminescent light sources
Aluminum alloy compounds as wide band gap semiconductors for electroluminescent light sources
Chicotka, R. J.↗
High field CdS detector for infrared radiation
New and highly sensitive method of detecting infrared irradiation makes possible solid state infrared detector which is more sensitive near room temperature than usual photoconductive low band gap semiconductor devices. Reconfiguration of high field domains in cadmium sulphide crystals provides basis for discovery.
Tyagi, R. C.↗
Flight test of an erectable spacecraft used for decelerator testing at simulated Mars entry conditions
A 55 foot diameter disk-gap-band parachute was deployed behind an expandable 15 foot diameter, 120 deg blunted-cone simulated spacecraft. The spacecraft was carried to altitude in the folded condition. An automatic control system kept the folded spacecraft pointing in the desired direction after booster separation. The aeroshell was then erected at the desired conditions by ground command. When the desired parachute test conditions were reached, another ground command deployed the test parachute. The test Mach number and dynamic pressure obtained at the parachute peak load were 2.62 and 19.4 pounds per square foot respectively. A large disturbance after aeroshell erection caused a large angle of attack to exist at parachute deployment. Methods of preventing this disturbance are discussed.
Henning, A. B.↗
Properties of crystalline bismuth selenide and its use as a Hall effect magnetometer
Single crystals of n-type Bi2Se3 grown by the Bridgman technique are found to make excellent Hall effect magnetometers. Plots of Hall resistivity sub yx against magnetic field B to 10 tesla are linear to within 1 percent. Furthermore, the slope of the sub yx against B curve varies by about 1 percent in the region 1.1 to 35 K and by less than 20 percent in the region 1.1 to 300 K. Analysis of galvanomagnetic measurements indicate the samples have semimetallic densities of approximately 10 to the 25th power/cu cm, with two band conduction and near carrier compensation. Reflectivity measurements suggest a band gap of approximately 0.08 eV for the samples. The temperature dependence of mobility is also measured. A series of 50 direct immersions into liquid helium and liquid nitrogen demonstrate the reliability of Bi2Se3 magnetometers for cryogenic use.
Wollam, J. A.↗
Balloon launched decelerator test program: Post-test test report
Balloon Launched Decelerator Test (BLDT) flights were conducted during the summer of 1972 over the White Sands Missile Range. The purpose of these tests was to qualify the Viking disk-gap band parachute system behind a full-scale simulator of the Viking Entry Vehicle over the maximum range of entry conditions anticipated in the Viking '75 soft landing on Mars. Test concerns centered on the ability of a minimum weight parachute system to operate without structural damage in the turbulent wake of the blunt-body entry vehicle (140 deg, 11.5 diameter cone). This is the first known instance of parachute operation at supersonic speeds in the wake of such a large blunt body. The flight tests utilized the largest successful balloon-payload weight combination known to get to high altitude (120kft) where rocket engines were employed to boost the test vehicle to supersonic speeds and dynamic pressures simulating the range of conditions on Mars.
Dickinson, D.↗
The Viking decelerator system - An overview.
The Viking mission to place an instrumented lander on Mars in 1976 includes an aerodynamic decelerator as part of the landing sequence. Development of the decelerator, a single-stage mortared disk-gap-band parachute, began in 1965 for the Voyager project and culminated in the flight qualification of the decelerator system for the Viking mission in 1972. This paper summarizes the research, development, and qualification effort. The special operating conditions and the constraints imposed by the Viking mission and the Mars atmosphere, their effects on the decelerator system, and the solution of the resulting technical problems are briefly described.
Gillis, C. L.↗
Development of the Viking parachute configuration by wind tunnel investigation.
Several experimental investigations to obtain the drag performance of 10% scale-model disk-gap-band-type parachute assemblies trailing in the Viking forebody wake were conducted over the range of Mach 0.2 to 2.6. The wind-tunnel tests varied both the canopy trailing distance and ratio of suspension line length to canopy diameter. The data obtained permitted optimization of both parameters. Parachute drag performance in the forebody wake is markedly degraded transonically beginning at Mach 0.6, reaching a minimum value at Mach 1.0, then approaches the subsonic value for the selected configuration as Mach number is increased to 1.4. Further increase in Mach number causes the drag coefficient to again decline. A 20% increase in parachute-alone transonic drag coefficient was obtained by increasing suspension-line length ratio from 1.16 to 1.73.
Steinberg, S.↗
Qualification flight tests of the Viking decelerator system.
The Balloon Launched Decelerator Test (BLDT) series conducted at White Sands Missile Range (WSMR) during July and August of 1972 flight qualified the NASA Viking '75 decelerator system at conditions bracketing those expected for Mars. This paper discusses the decelerator system design requiremnts, compares the test results with prior work, and discusses significant considerations leading to successful qualification in earth's atmosphere. The Viking decelerator system consists of a single-stage mortar-deployed 53-foot nominal diameter disk-gap-band parachute. Full-scale parachutes were deployed behind a full-scale simulated Viking vehicle at Mach numbers from 0.47 to 2.18 and dynamic pressures from 6.9 to 14.6 psf. Analyses show that the system is qualified with sufficient margin to perform successfully for the Viking mission.
Moog, R. D.↗
The Viking mortar - Design, development, and flight qualification.
Approximately 25,400 ft above the local surface of Mars, a radar height sensor fires the Viking mortar, which ejects a 53-ft D sub o disk-gap-band (DGB) parachute. The parachute decelerates and stabilizes the Viking lander sufficiently for the terminal engine system to take over and effect a soft landing. The general design and environmental requirements for the mortar system are presented; various illustrations of the mortar components and how the mortar system functions also are presented. Primary emphasis is placed on manufacturing, developing, and qualification testing of the mortar system.
Brecht, J. P.↗
Drag and stability characteristics of high-speed parachutes in the transonic range.
The results of wind tunnel tests of three parachute configurations in the wake of a cone-cylinder are presented. The tests were conducted to extend the drag and stability characteristics of selected parachutes through the transonic speed range. The configurations studied were the hemisflo ribbon, the cross, and the disk-gap-band types. The results are presented as the variation of the parachute drag coefficient with Mach number. General stability characteristics of the parachutes are discussed. The results are then correlated with some published subsonic and supersonic data.
Alexander, W. C.↗
Surface-state spectra from thick-oxide MOS tunnel junctions
The conductance and capacitance of thick-oxide MOS tunnel junctions (SiO2 thickness 40 to 65 A) have been measured from 35 Hz to 210 kHz. It is demonstrated that the use of a thick-oxide MOS tunnel junction makes it possible to obtain the surface-state data throughout the whole silicon band gap with better resolution and better sensitivity than the conventional MOS capacitance techniques. A slight departure from equilibrium may occur in the voltage range where large tunnel current flows. Corrections to the energy scale must be made in this voltage range. A method for the evaluation of the junction quality is discussed. The simplified equivalent circuits necessary for the calculation of surface-state data are constructed under various bias conditions by an approach different from that used in a previously published work. The present work supports the model that at least some of the observed surface states are a consequence of the diffusion of contact metals into the oxide.
Ma, T. P.↗
Laser-to-electricity energy converter for short wavelengths
Short-wavelength energy converter can be made using Schottky barrier structure. It has wider band gap than p-n junction silicon semiconductors, and thus it has improved response at wavelengths down to and including ultraviolet region.
Stirn, R. J.↗
Flight tests of Viking parachute system in three Mach number regimes. 2: Parachute test results
Tests of the Viking 16.15-meter nominal-diameter disk-gap-band parachute were conducted at Mach number and dynamic pressure conditions which bracketed the range postulated for the Viking '75 mission to Mars. Parachutes were deployed at supersonic, transonic, and subsonic speeds behind a simulated Viking entry capsule. All parachutes successfully deployed, inflated, and exhibited sufficient drag and stability for mission requirements. Basic parachute data including loads, drag coefficients, pull-off angles, and canopy area ratios are presented. Trajectory reconstruction and onboard camera data methods were combined to yield continuous histories of both parachute and test-vehicle angular motions which are presented for the period from parachute deployment through steady inflation.
Bendura, R. J.↗
Drag and stability characteristics of a variety of reefed and unreefed parachute configurations at Mach 1.80 with an empirical correlation for supersonic Mach numbers
An investigation was conducted at Mach 1.80 in the Langley 4-foot supersonic pressure tunnel to determine the effects of variation in reefing ratio and geometric porosity on the drag and stability characteristics of four basic canopy types deployed in the wake of a cone-cylinder forebody. The basic designs included cross, hemisflo, disk-gap-band, and extended-skirt canopies; however, modular cross and standard flat canopies and a ballute were also investigated. An empirical correlation was determined which provides a fair estimation of the drag coefficients in transonic and supersonic flow for parachutes of specified geometric porosity and reefing ratio.
Couch, L. M.↗
Optical absorption components of light-modulated absorption spectrum of CdS
The amplitude and decay coefficient of light-induced modulation of absorption (LIMA) was measured as a function of wavelength from 535 to 850 nm for single-crystal CdS. The decay coefficient exhibited a discontinuous resonance at 710 nm which was due to the overlap and cancellation of two opposing absorption changes. A method was developed to separate these opposing absorption changes using the measured decay coefficients. The discrete-level-to-band energy for one absorption change was found to be 1.64 eV. An improved model was developed which contains two associated levels in the band gap separated by 0.32 eV.
Conway, E. J.↗
Flight test of a spin parachute for use with a Super Arcas sounding rocket
The development and flight testing of a specially configured 16.6 ft Disc Band Gap (DBG) Spin Parachute is discussed. The parachute is integrated with a modified Super Arcas launch vehicle. Total payload weight was 17.6 lbs including the Spin Parachute and a scientific payload, and lift-off weight was 100.3 lbs. The Super Arcas vehicle was despun from 18.4 cps. After payload separation at 244,170 ft the Spin Parachute and its payload attained a maximum spin rate of 2.4 cps. Total suspended weight of the Spin Parachute and its payload was 14.64 lbs.
Silbert, M. N.↗