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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 1,027 records · Page 57
All sourcesNASA NTRSDOE OSTI
NASA NTRS1974

Separated flow over bodies of revolution using an unsteady discrete-vorticity cross wake. Part 2: Computer program description

A method is developed to determine the flow field of a body of revolution in separated flow. The computer was used to integrate various solutions and solution properties of the sub-flow fields which made up the entire flow field without resorting to a finite difference solution to the complete Navier-Stokes equations. The technique entails the use of the unsteady cross flow analogy and a new solution to the two-dimensional unsteady separated flow problem based upon an unsteady, discrete-vorticity wake. Data for the forces and moments on aerodynamic bodies at low speeds and high angle of attack (outside the range of linear inviscid theories) such that the flow is substantially separated are produced which compare well with experimental data. In addition, three dimensional steady separated regions and wake vortex patterns are determined. The computer program developed to perform the numerical calculations is described.

Marshall, F. J.↗
NASA NTRS1973

Trajectory description

The Mariner 9 spacecraft was launched by an Atlas/Centaur launch vehicle (AC-23) on a direct-ascent trajectory from the Air Force Eastern Test Range (AFETR) launch complex 36B on May 30, 1971. Liftoff occurred at 22 h 23 min 04.5 s GMT, slightly more than 6 min after the opening of a 60-min launch window. The vehicle rose vertically for approximately 15 s, during which time, a programmed roll to a launch azimuth of 92.74 deg was performed. After the initial vertical rise, the vehicle, guided by the open-loop Atlas autopilot, began to pitch over into a zero-lift trajectory. The first of three main powered phases was terminated by booster engine cutoff (BECO) at 22 h 25 min 35.5 s. After the Atlas booster engine package was jettisoned 3 s later, the flight continued under the power of the Atlas sustainer engine and guided by the Centaur guidance system operating in a closed-loop mode.

Webb, W. A.↗
NASA NTRS1974

Hypersonic ramjet experiment project. Phase 1: Computer program description, ramjet and scramjet cycle performance

A computer program was developed to describe the performance of ramjet and scramjet cycles. The program performs one dimensional calculations of the equilibrium, real-gas internal flow properties of the engine. The program can be used for the following: (1) preliminary design calculation and (2) design analysis of internal flow properties corresponding to stipulated flow areas. Only the combustion of hydrogen in air is considered in this case.

Jackson, R. J.↗
NASA NTRS1974

Altitude determination and descriptive analysis of clouds on ERTS-1 multispectral photography

A simple method to determine the approximate altitude of clouds is described, with the objective of refining their classification using only marginal data from the photographs. Results of the application of this method on photographs of the Goajira Peninsula, Paraguana Peninsula and the Central Coast of Venezuela are presented. Here, the altitudes computed are used to classify clouds and to identify the genus of others without typical form. Instability of air masses through clouds vertical development, and wind direction as well as other local climatic characteristics such as moisture content, loci of condensation, area, etc. are determined using repetitive coverage for the time interval of the photography. Applications for the regional and urban planning (including airport location and flights schedule) and natural resources evaluation are suggested.

Albrizzio, C.↗
NASA NTRS1974

A brief description of the Medical Information Computer System (MEDICS)

The Medical Information Computer System (MEDICS) is a time shared, disk oriented minicomputer system capable of meeting storage and retrieval needs for the space- or non-space-related applications of at least 16 simultaneous users. At the various commercially available low cost terminals, the simple command and control mechanism and the generalized communication activity of the system permit multiple form inputs, real-time updating, and instantaneous retrieval capability with a full range of options.

Moseley, E. C.↗
NASA NTRS1974

Description of the attitude control, guidance and navigation space replaceable units for automated space servicing of selected NASA missions

Control elements such as sensors, momentum exchange devices, and thrusters are described which can be used to define space replaceable units (SRU), in accordance with attitude control, guidance, and navigation performance requirements selected for NASA space serviceable mission spacecraft. A number of SRU's are developed, and their reliability block diagrams are presented. An SRU assignment is given in order to define a set of feasible space serviceable spacecraft for the missions of interest.

Chobotov, V. A.↗
NASA NTRS1974

Four-D global reference atmosphere technical description, part 1

An empirical atmospheric model was developed which generates values for pressure, density, temperature, and winds from surface levels to orbital altitudes. The output parameters consist of components for: (1) latitude, longitude, and altitude dependent monthly and annual means; (2) quasi-biennial oscillations; and (3) random perturbations to simulate partially the variability due to synoptic, diurnal, planetary wave, and gravity wave variations. Quasi-biennial and random variation perturbations are computed from parameters determined from various empirical studies and are added to the monthly mean values. This model has been developed as a computer program called PROFILE which can be used to generate altitude profiles of atmospheric parameters along any simulated trajectory through the atmosphere. The PROFILE program was developed for design applications in the space shuttle program. Other applications of the model are discussed, such as for global circulation and diffusion studies, and for generating profiles for comparison with other atmospheric measurement techniques, (e.g. satellite measured temperature profiles).

Justus, C. G.↗
NASA NTRS1974

Lightning damage to a general aviation aircraft: Description and analysis

The damage sustained by a Beechcraft King Air Model B90 aircraft by a single lightning discharge is presented and analyzed. The incident occurred during landing approach at Jackson, Michigan, on Feb. 19, 1971. In addition to the usual melted-metal damage at the lightning attachment points, there was severe implosion-type damage over a large area on the lower right side of the aircraft and impact- and crushing-type damage on the upper and lower surfaces on the left wingtip near the trailing edge. Analyses indicate that the implosion-type damage was probably caused by lightning-generated shock waves, that the impact-and crushing-type damage was caused by magnetic forces, and that the lightning discharge was a multiple strike with at least 11 strokes separated in time by about 4.5 milliseconds. The evidence indicates that the lightning discharge was rather different from the average in character severity.

Hacker, P. T.↗
NASA NTRS1974

MIDAS, prototype Multivariate Interactive Digital Analysis System, phase 1. Volume 1: System description

The MIDAS System is described as a third-generation fast multispectral recognition system able to keep pace with the large quantity and high rates of data acquisition from present and projected sensors. A principal objective of the MIDAS program is to provide a system well interfaced with the human operator and thus to obtain large overall reductions in turnaround time and significant gains in throughput. The hardware and software are described. The system contains a mini-computer to control the various high-speed processing elements in the data path, and a classifier which implements an all-digital prototype multivariate-Gaussian maximum likelihood decision algorithm operating at 200,000 pixels/sec. Sufficient hardware was developed to perform signature extraction from computer-compatible tapes, compute classifier coefficients, control the classifier operation, and diagnose operation.

Kriegler, F. J.↗
NASA NTRS1974

Skylab neutron environment experiment (Science Demonstration SD-34 (TV108)). Description and preliminary results

Neutron and proton induced radioactivity at various locations within Skylab were measured. Samples of five metals were formed into activation packets and deployed at the following locations on the Skylab 4 mission: orbital workshop film vault, water storage tank, and two opposing orbital workshop internal locations. Radioactive nuclides were produced in the packets by nuclear interactions of high-energy protons and secondary neutrons within Skylab. Low-level gamma ray spectroscopy measurements were made on the returned packets to determine the incident neutron and proton fluxes and spectra and their variations with mass distribution.

Fishman, G. J.↗
NASA NTRS1974

Description of the meteoroid detection experiment flown on the Pioneer 10 and 11 Jupiter flyby missions

The meteoroid detection experiment has the objective of measuring the population of 10 to the minus 9th power and 10 to the minus 8th power grams mass particles in interplanetary space with emphasis on making these measurements in the Asteroid Belt. The instrument design, which uses the pressurized-cell-penetration detection technique, and the tests involved in obtaining a flight-qualified instrument are described. The successful demonstration of flight-quality penetration detectors to function properly under long-term simulated space environments is also described.

Oneal, R. L.↗
NASA NTRS1973

Apollo 17 lunar samples - Chemical and petrographic description

Some of the Apollo 17 rocks have the cataclastic, highly crushed textures common in the Apollo 16 return. Many are crystalline breccias whose petrographic characteristics indicate varying degrees of recrystallization or partial melting. Others are friable and dark gray like the many regolith breccias of previous missions. A few have the coarse-grained igneous textures typically developed during the slow crystallization from basaltic melts. Petrographic and soil characteristics are discussed together with the results of X-ray fluorescence analyses.

Source record↗
NASA NTRS1973

The Space Shuttle System description, operations, and payload capabilities

General characteristics of the Space Shuttle System are presented with overall capabilities and operating characteristics detailed. Mission operations and performance baselines are presented. The relationships between orbital parameters and payload capabilities are highlighted. On-orbit scientific and applications operating modes are briefly reviewed and methods of achieving a versatile payloads program using standard payload carriers are discussed.

Heberlig, J. C.↗
NASA NTRS1973

Sample 67955 - A description and a problem

Clasts in breccia sample 67955 contain relatively coarse olivine and plagioclase in part enveloped by poikilitic hypersthene and diopside. This distinctive texture is concluded to result from high temperature crystallization in the presence of a fluid phase, probably a silicate melt. A problem posed by this rock is whether the bulk chemistry, characterized by a high Mg/Fe ratio but low total Fe + Mg, is the result of primary igneous processes on the moon or whether it is the residual end product of a multiple distillation process resulting from repeated meteorite impacts.

Hollister, L. S.↗
NASA NTRS1973

A description of a general use automated data reduction system

A data system developed for use in tests in arc jet facilities has the flexibility to accommodate various types of data, time resolution, and number of data signals. Data are tape-recorded, because a direct link to the IBM 360/67 computer is prohibited for safety reasons. The system is analogous to manual data reduction to promote user understanding and acceptance. Data computations may be performed in an interactive ('conversational') mode, for minimum delay in data reduction, or by card input. Reduced data are listed and also stored for plotting of further computational use. Operational costs of the system are reasonable, and both large and small data reduction tasks are handled readily.

Wakefield, R. M.↗
NASA NTRS1974

The experimental clean combustor program - Description and status

The experimental clean combustor program is a contract effort with primary objectives including the generation and demonstration of technology for development of advanced commercial CTOL aircraft engines with lower exhaust emissions than current aircraft, and the demonstration of this technology in full scale engines in 1976. The program is being conducted in three phases. These consist of screening of low pollutant combustors, refinement of the best combustors, and engine demonstration of the best combustors. Pollution goals are emission index values of 20 and 4 for carbon monoxide and unburned hydrocarbons respectively at engine idle conditions, and an oxides of nitrogen emission index level of 10 at engine takeoff conditions. Pollution reduction approaches which are being investigated include multiple burning zone combustors, investigations of improved fuel distribution, and preparation and the staging of combustor airflow.

Niedzwiecki, R. W.↗