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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 1,729 records · Page 96

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NASA NTRS1977

System for producing chroma signals

A method for obtaining electronic chroma signals with a single scanning-type image device is described. A color multiplexed light signal is produced using an arrangement of dichroic filter stripes. In the particular system described, a two layer filter is used to color modulate external light which is then detected by an image pickup tube. The resulting time division multiplexed electronic signal from the pickup tube is converted by a decoder into a green color signal, and a single red-blue multiplexed signal, which is demultiplexed to produce red and blue color signals. The three primary color signals can be encoded as standard NTSC color signals.

Vorhaben, K. H.↗

NASA NTRS1977

Reduction of the equation for lower hybrid waves in a plasma to a nonlinear Schroedinger equation

Equations describing the nonlinear propagation of waves in an anisotropic plasma are rarely exactly soluble. However it is often possible to make approximations that reduce the exact equations into a simpler equation. The use of MACSYMA to make such approximations, and so reduce the equation describing lower hybrid waves into the nonlinear Schrodinger equation which is soluble by the inverse scattering method is demonstrated. MACSYMA is used at several stages in the calculation only because there is a natural division between calculations that are easiest done by hand, and those that are easiest done by machine.

Karney, C. F. F.↗

NASA NTRS1976

A comparison of the aerodynamic characteristics at transonic speeds of four wing-fuselage configurations as determined from different test techniques, 4 October 1960

The high speed aerodynamic characteristics of a family of four wing-fuselage configurations of 0, 35, 45, and 60 deg sweepback were determined from transonic bump model tests that were conducted in the Langley high speed 7 by 10 foot tunnel; sting supported model tests were conducted in the Langley 8 foot high speed tunnel and in the Langley high speed 7 by 10 foot tunnel, and rocket model tests were conducted by the Langley Pilotless Aircraft Research Division. A complementary study of the effect of Mach number gradients and streamline curvature on bump results is also included. The qualitative data obtained from the various test facilities for the wing-fuselage configurations were in essential agreement as regards the relative effects of sweepback and Mach number except for drag at zero lift. Quantitatively, important differences were present.

Donlan, C. J.↗

NASA NTRS1977

LACIE: Wheat yield models for the United States, revision A

For abstract, see volume 1 N77-30577. The enclosed maps indicate the areal coverage of the various models for spring (durum and other spring) and winter wheat. The given regions are the combination of several climatic divisions and many times comprise an entire state.

Source record↗

NASA NTRS1976

Studies on the nature of plasma growth hormone

The paper presents further evidence for the existence of two discrete forms of growth hormone in human plasma, one which is detectable by both radioimmunoassay and bioassay and is immunoreactive, and the other, termed 'bioactive', which is detected by tibial bioassay but shows little reactivity with currently available antisera to pituitary growth hormone. The same division of immunoactive and bioactive growth hormone occurs in rats, though with less disparity. Tests on rats indicated that the bioactive hormone is preferentially released into jugular vein plasma and that plasma concentrations of the bioactive hormone can be enhanced by insulin administration. The bioactive hormone was detectable by tibial assays in Cohn fractions IV, IV-1, and IV-4, and could be concentrated about 40-fold by fractionation with (NaPO3)6 and (NH4)2SO4.

Ellis, S.↗

NASA NTRS1976

Recovery from a tumbling condition in space

The Space Division of Rockwell International has examined means for arresting the motion of an out-of-control tumbling manned spacecraft. Twenty-three different concepts for checking the tumbling by using a rescue Space Shuttle have been evaluated. The most practical of these approaches were a stick-on rocket concept and a water-stream concept. Analysis of these two methods, which are described in this paper, shows that they are feasible and can be used to stop the worst-case tumbling considered and allow rescue of the crew with one Shuttle flight.

Canetti, G. S.↗

NASA NTRS1976

Singularity-free extraction of a quaternion from a direction-cosine matrix

A computer algorithm for extracting a quaternion from a direction-cosine matrix (DCM) is described. The quaternion provides a four-parameter representation of rotation, as against the nine-parameter representation afforded by a DCM. Commanded attitude in space shuttle steering is conveniently computed by DCM, while actual attitude is computed most compactly as a quaternion, as is attitude error. The unit length of the rotation quaternion, and interchangeable of a quaternion and its negative, are used to advantage in the extraction algorithm. Protection of the algorithm against square root failure and division overflow are considered. Necessary and sufficient conditions for handling the rotation vector element of largest magnitude are discussed

Klumpp, A. R.↗

NASA NTRS1975

Digital speech processing for the Space Shuttle program

This paper describes the voice digitization technique which has been selected for the Space Shuttle program. The selected approach is compatible with a time-division multiplexing scheme which combines one or two digital voice channels with commands prior to transmission over an RF uplink or with telemetry prior to transmission over an RF downlink.

Batson, B. H.↗

NASA NTRS1976

Fireball end heights - A diagnostic for the structure of meteoric material

An earlier analysis of Prairie Network fireball trajectory data failed to discriminate between the varieties of meteoric materials that are thought to be present. The Lost City meteorite event offers another calibration of the fireball data and prompts a reanalysis intended to distinguish between ordinary chondritic meteorites and the more fragile early-type carbonaceous chondrites. The carbonaceous material is expected to ablate more readily and have shorter trajectories or higher end heights. Observational error and natural dispersion in the structures produce severe smoothing effects, and the end-height diagnostic is, in itself, not entirely convincing. However, after making a tentative division of the data, one can discern differences in orbits and beginning heights among the three end-height groups. These are consistent with expectations of the behavior of chondritic stones (group I), weak carbonaceous chondrites (group II), and still more fragile cometary material (group III). It is concluded that if the carbonaceous material occurs in reasonable abundance among the fireballs, it has been properly identified by this analysis.

Ceplecha, Z.↗

NASA NTRS1976

Simulation of fluidized bed combustors. I - Combustion efficiency and temperature profile

A chemical engineering analysis is made of fluidized-bed combustor (FBC) performance, with FBC models developed to aid estimation of combustion efficiency and axial temperature profiles. The FBC is intended for combustion of pulverized coal and a pressurized FBC version is intended for firing gas turbines by burning coal. Transport phenomena are analyzed at length: circulation, mixing models, drifting, bubble wake lift, heat transfer, division of the FB reactor into idealized mixing cells. Some disadvantages of a coal FBC are pointed out: erosion of immersed heat-transfer tubing, complex feed systems, carryover of unburned coal particles, high particulate emission in off-streams. The low-temperature bed (800-950 C) contains limestone, and flue-gas-entrained SO2 and NOx can be kept within acceptable limits.

Horio, M.↗

NASA NTRS1977

Numerical solution for subcritical flows by a transonic integral equation method

The method presented makes use of a division of the region of integration into closed rectangular elements. The velocity is taken to be constant in each element. The integral equation is reduced to a matrix equation which can be solved by an appropriate iteration approach. The derivation and solution of the matrix equation are discussed and the matrix elements are considered. The described concepts were implemented for a nonlifting parabolic-arc airfoil.

Ogana, W.↗

NASA NTRS1976

Seismic investigation of the lunar interior

The velocity and attenuation structure of the moon below the crust is examined using surface events. The moon is divided into an upper mantle and a lower mantle, the division at a depth of about 500 km being marked by a reflector identified on polarization filtered record sections. The upper mantle has a P-wave velocity of about 8 km/sec, a Poisson's ratio of about 0.25 and a Q for P waves of about 5000. This region contains no partial melt and is depleted in volatiles, notably water. The lower mantle has a lower S-wave velocity and probably a lower P-wave velocity than the upper mantle, with a Poisson's ratio of about 0.34. The lower mantle has a Q for P waves of approximately 1500, substantially lower than the upper mantle but probably still high enough to preclude partial melting. The velocity structure and the current value of the moment of inertia factor indicate an increase of density below about 500 km, perhaps due to an increase in iron content. We do not have any information directly pertaining to seismic velocities below 1000 km depth.

Dainty, A. M.↗

NASA NTRS1976

Methods, advantages, and limitations of compositing photographic images

Basic procedures used in compositing photographic images to increase their information content are briefly discussed. A new method for calculating exposure time for each image is presented. A portion of the density coordinate of the characteristic curve of the film on which the exposures are to be made is divided into as many divisions as there are images to be superimposed. Lines are drawn from the intersections of these density increments with the characteristic curve to the log exposure for each image. A study of the ability of workers to superimpose plant images with a projected scale of one arcsec per millimeter has shown that image smearing due to alignment errors in a composite will not exceed about 0.15 arcseconds if images are composited by an adept operator.

Jones, S. E.↗

NASA NTRS1976

Space Shuttle Orbiter crash and rescue information - Basic characteristics of the Space Shuttle system

Major fire and rescue activity procedures developed for the Space Shuttle Orbiter are reproduced, together with diagrams of the Orbiter's ejection seat and of emergency egress-ingress hatches and blowout panels. Duties assigned to the Manager of the Fire, Crash and Rescue division of the Space Shuttle Program are discussed, including training of both ground and flight personnel in accordance with the Orbiter Crash Rescue Information manual. The special problem of providing a means of egress and rescue for the flight and ground crews of the Orbiter while it is in the piggyback configuration on top the Boeing 747 carrier was solved by use of a modified 85-foot articulated boom.

Gray, N. C.↗

NASA NTRS1977

Linear aerospike engine

A description is presented of a dual-fuel modular split-combustor linear aerospike engine concept. The considered engine represents an approach to an integrated engine for a reusable single-stage-to-orbit (SSTO) vehicle. The engine burns two fuels (hydrogen and a hydrocarbon) with oxygen in separate combustors. Combustion gases expand on a linear aerospike nozzle. An engine preliminary design is discussed. Attention is given to the evaluation process for selecting the optimum number of modules or divisions of the engine, aspects of cooling and power cycle balance, and details of engine operation.

Kirby, F. M.↗

NASA NTRS1977

Flight simulators. Part 1: Present situation and trends. Part 2: Implications for training

The present situation and developments in the technology of flight simulators based on digital computers are evaluated from the standpoint of training airline flight crews. Areas covered are minicomputers and their advantages in terms of cost, space and time savings, software data packets, motion simulation, visual simulation and instructor aids. The division of training time between aircraft and simulator training and the possible advantages from increased use of simulators are evaluated.

Hass, D.↗

NASA NTRS1977

Rocketdyne's advanced coal slurry pumping program

The Rocketdyne Division of Rockwell International Corporation is conducting a program for the engineering, fabrication, and testing of an experimental/prototype high-capacity, high-pressure centrifugal slurry feed pump for coal liquefaction purposes. The abrasion problems in a centrifugal slurry pump are primarily due to the manner in which the hard, solid particles contained in the slurry are transported through the hydraulic flow passages within the pump. The abrasive particles can create scraping, grinding, cutting, and sandblasting effects on the various exposed parts of the pump. These critical areas involving abrasion and impact erosion wear problems in a centrifugal pump are being addressed by Rocketdyne. The mechanisms of abrasion and erosion are being studied through hydrodynamic analysis, materials evaluation, and advanced design concepts.

Davis, D. E.↗

NASA NTRS1977

Meteorological support for remote sensing programs

Many earth-oriented remote sensing spacecraft and aircraft programs are affected by the presence of clouds. Like aerial photography, they require clear or mostly clear skies. To cope with the cloud problem, the National Weather Service through its Spaceflight Meteorology Group (SMG) of the Space Operations Support Division makes cloud cover forecasts, as part of its specialized weather service for various NASA remote sensing and other programs. Forecasting requirements vary in time from a few hours out to several days and in aerial extent from a particular locality to nearly global in coverage. Depending on the stage of program development, some remote sensing programs may involve special climatological studies for planning purposes or need ground-truth data for comparison with remotely sensed information. The importance of computer and weather satellite products to the SMG meteorologist is discussed and the nature of SMG's weather support of past, present, and future remote sensing programs is described.

Cox, J. L.↗