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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 505 records · Page 28
All sourcesNASA NTRSDOE OSTI
NASA NTRS1979

Thrust oscillations of the Space Shuttle solid rocket Booster motor during static tests

Thrust oscillations have occurred during static tests of Space Shuttle Booster solid rocket motors. These oscillations in measured axial thrust occurred primarily near 15 Hz; these oscillations late in the motor burn reach magnitudes up to approximately + or - 3% of motor thrust. The phenomenon has consistently occurred on the four demonstration motors which have been static tested and appears to be associated with small amplitude, 15 Hz pressure oscillations inside the motor. The source of the pressure oscillations is thought to be associated with the fundamental longitudinal acoustic resonance of the motor at 15 Hz. These thrust oscillations potentially can impact the design of the Space Shuttle vehicle structure. The demonstration motors have been instrumented with an array of transducers to aid in understanding the phenomenon. In addition to measuring axial and lateral thrust of the motor, pressure transducers were located to measure chamber pressure oscillations at the forward dome. Accelerometers and extensometers have measured motions of the structure. A modal survey was conducted on a fired motor to identify its structural dynamic characteristics, and these data were used to validate mathematical models of the motor in the static test facility.

Mason, D. R.↗
NASA NTRS1979

Evidence for explosive volcanic density currents on certain Martian volcanoes

The morphologies of certain of the smaller Martian volcanoes are discussed as possible results of explosive volcanic density currents. An examination of newly-photographed flank and caldera features of the Martian volcanoes Ceraunius Tholus, Uranius Tholus, Uranius Patera and Hecates Tholus, including steep slope angles, Krakatoa-type caldera morphologies, erosional features (radial channels and anastamosing gullies) and constructional features (blanketed flanks and possible lava deltas) reveals their similarity to terrestrial cones and composite volcanoes such as Barcena Volcano. Crater age data from the surface of Martian domes and shields indicates that such explosive activity occurred more frequently early in Martian geologic history, consistent with the view that the volcanic density currents were base surges rather than nuees ardentes, with the melting of permafrost supplying the water required in base surge generation.

Reimers, C. E.↗
NASA NTRS1981

Economical ultraviolet radiometer

Inexpensive, cosine-corrected radiometer measures ultraviolet radiation. In field use, instrument tests materials for effects of ultraviolet exposure and studies solar-cell degradation. It consists of cup-shaped diaphragm and diffusing dome for corrected response, two filters that select wavelength range, and silicon solar cell. Filters control response within passband of 300 to 400 nm.

Seaman, C. H.↗
NASA NTRS1979

Quiet Clean Short-haul Experimental Engine (QCSEE). Double-annular clean combustor technology development report

A sector combustor technology development program was conducted to define an advanced double annular dome combustor sized for use in the quiet clean short haul experimental engine (QCSEE). A design which meets the emission goals, and combustor performance goals of the QCSEE engine program was developed. Key design features were identified which resulted in substantial reduction in carbon monoxide and unburned hydrocarbon emission levels at ground idle operating conditions, in addition to very low nitric oxide emission levels at high power operating conditions. Their significant results are reported.

Bahr, D. W.↗
NASA NTRS1980

Geometric modeling and analysis of large latticed surfaces

The application of geometrical schemes, similar to geodesic domes, to large spherical antenna reflectors was investigated. The shape and size of flat segmented latticed surfaces which approximate general shells of revolution, and in particular spherical and paraboloidal reflective surfaces, were determined. The extensive mathematical and computational geometric analyses of the reflector resulted in the development of a general purpose computer program capable of generating the complete design parameters of the dish. The program also includes a graphical self contained subroutine for graphic display of the required design.

Nayfeh, A. H.↗
NASA NTRS1980

High temperature underground thermal energy storage system for solar energy

The activities feasibility of high temperature underground thermal storage of energy was investigated. Results indicate that salt cavern storage of hot oil is both technically and economically feasible as a method of storing huge quantities of heat at relatively low cost. One particular system identified utilizes a gravel filled cavern leached within a salt dome. Thermal losses are shown to be less than one percent of cyclically transferred heat. A system like this having a 40 MW sub t transfer rate capability and over eight hours of storage capacity is shown to cost about $13.50 per KWh sub t.

Collins, R. E.↗
NASA NTRS1979

Space Shuttle solid rocket booster

Details of the design, operation, testing and recovery procedures of the reusable solid rocket boosters (SRB) are given. Using a composite PBAN propellant, they will provide the primary thrust (six million pounds maximum at 20 s after ignition) within a 3 g acceleration constraint, as well as thrust vector control for the Space Shuttle. The drogues were tested to a load of 305,000 pounds, and the main parachutes to 205,000. Insulation in the solid rocket motor (SRM) will be provided by asbestos-silica dioxide filled acrylonitrile butadiene rubber ('asbestos filled NBR') except in high erosion areas (principally in the aft dome), where a carbon-filled ethylene propylene diene monomer-neopreme rubber will be utilized. Furthermore, twenty uses for the SRM nozzle will be allowed by its ablative materials, which are principally carbon cloth and silica cloth phenolics.

Hardy, G. B.↗
NASA NTRS1979

The chronology of the martian volcanoes

The volcanoes of Mars have been divided into three groups based on morphology: basaltic shields, domes and composite cones, and highland patera. A fourth group can be added to include the volcano-tectonic depressions. Using crater counts and the absolute chronology of Soderblom, an attempt is made to estimate the history of the volcanoes. Early in the martian history, about 2.5 b.y. ago, all three styles of volcanoes were active at various locations on the surface. At approximately 1.7-1.8 b.y. ago a transition occurred in the style and loci of volcanic construction. Volcanoes of younger age appear to be only of the basaltic shield group and are restricted to the Tharsis region. This same transition was noted by a change in the style of the basaltic shield group. Older shields were small low features, while the younger shields are significantly broader and taller.

Plescia, J. B.↗
NASA NTRS1979

Alphonsus-type dark-halo craters - Morphology, morphometry and eruption conditions

The Alphonsus dark-halo craters are sites of volcanic eruptions with a characteristic crater radius of approximately 1 km. They are characterized by dark haloes ranging from 3 to 4 km, by substantial amounts of nonjuvenile material within the deposits, and by a lack of any associated lava flows or prominent constructional features, such as cones or domes. In the present paper, possible eruption styles are analyzed, using these observational constraints. It is concluded that an eruption process analogous to terrestrial volcanian explosive activity provides the most reasonable explanation for the characteristics of the deposits. The dark-halo craters appear to have formed contemporaneously with the emplacement of lavas in the adjacent Mare Nubium.

Head, J. W., III↗
NASA NTRS1980

Performance of fused silica as a filter in a wide field-of-view earth radiation budget radiometer

The thermal response of the fused silica dome filter in an earth radiation budget WFOV shortwave channel conceptual design and the impact of that response on the channel measurement, is described. Attention is given to results from design definition and performance analysis studies. Consideration is given to problems associated with achieving the desired levels of confidence in a high accuracy filtered earth radiation budget WFOV radiometer. Finally, design approaches, ground calibration, and data reduction techniques that minimize measurement uncertainties are covered.

Cooper, J. E.↗
NASA NTRS1980

Welding of the external tank of the Space Shuttle

Welding processes and assembly techniques used in the fabrication of the external tank of the Space Shuttle are discussed. Each external tank consists of one liquid oxygen tank and one liquid hydrogen tank connected by an intertank skirt which is mechanically assembled; the fabrication of the external tank pressure vessel involves about 36,000 linear inches of weld required to join 138 pieces of 2219 aluminum. The discussion includes several innovations, such as building domes using the 1/4 panel assembly technique, which have been used in the fabrication of the tank.

Clover, F. R., Jr.↗
NASA NTRS1980

Spaceborne imaging radar - Geologic and oceanographic applications

Synoptic, large-area radar images of the earth's land and ocean surface, obtained from the Seasat orbiting spacecraft, show the potential for geologic mapping and for monitoring of ocean surface patterns. Structural and topographic features such as lineaments, anticlines, folds and domes, drainage patterns, stratification, and roughness units can be mapped. Ocean surface waves, internal waves, current boundaries, and large-scale eddies have been observed in numerous images taken by the Seasat imaging radar. This article gives an illustrated overview of these applications.

Elachi, C.↗
NASA NTRS1980

Experimental evaluation of combustor concepts for burning broad property fuels

A baseline CF6-50 combustor and three advanced combustor designs were evaluated to determine the effects of combustor design on operational characteristics using broad property fuels. Three fuels were used in each test: Jet A, a broad property 13% hydrogen fuel, and a 12% hydrogen fuel blend. Testing was performed in a sector rig at true cruise and simulated takeoff conditions for the CF6-50 engine cycle. The advanced combustors (all double annular, lean dome designs) generally exhibited lower metal temperatures, exhaust emissions, and carbon buildup than the baseline CF6-50 combustor. The sensitivities of emissions and metal temperatures to fuel hydrogen content were also generally lower for the advanced designs. The most promising advanced design used premixing tubes in the main stage. This design was chosen for additional testing in which fuel/air ratio, reference velocity, and fuel flow split were varied.

Kasper, J. M.↗
NASA NTRS1981

Low thrust chemical orbit to orbit propulsion system propellant management study

Low thrust chemical propulsion systems were sized for transfer of large space systems from LEO to GEO. The influence of propellant combination, tankage and insulation requirements, and propellant management techniques on the LTPS mass and volume were studied. Liquid oxygen combined with hydrogen, methane or kerosene were the propellant combinations. Thrust levels of 445, 2230, and 4450 N were combined with 1, 4 and 8 perigee burn strategies. This matrix of systems was evaluated using multilayer insulation and spray-on-foam insulation systems. Various combinations of toroidal, cylindrical with ellipsoidal domes, and ellipsoidal tank shapes were investigated. Results indicate that low thrust (445 N) and single perigee burn approaches are considerably less efficient than the higher thrust level and multiple burn strategies. A modified propellant settling approach minimized propellant residuals and decreased system complexity, in addition, the toroid/ellipsoidal tank combination was predicted to be shortest.

Dergance, R. H.↗
NASA NTRS1980

The satellites of Jupiter; Proceedings of the Fifty-seventh Colloquium, Kailua, Hawaii, May 13-16, 1980

Among the topics covered by the colloquium on the satellites of Jupiter are: the internal energy and thermophysics of the surface of Io, plume volcanism on Io, the photometric variability of Io, the near-surface flow of volcanic gases on Io, and the sodium emission cloud of Io and its north-south asymmetry. Also considered are: the physical processes and origins of Jupiter's ring and its possible effect on the Jovian inner plasmasphere, the composition of such moons of Jupiter as Amalthea, Ganymede, Europa and Callisto and their lithospheric and ice evolutions. Particular attention is given such topographic features as the domes and grooved terrain on Ganymede, water frost and ice, and the photometric properties of these outer satellites of Jupiter.

Burns, J. A.↗
NASA NTRS1981

The Tempe volcanic province of Mars and comparisons with the Snake River Plains of Idaho

The Tempe volcanic region of Mars, a relatively low plain of probable basaltic flood lava affinity, is shown to be comparable in many respects to features of the Snake River Plains of Idaho, including both scale and type of features observed. Superimposed upon the Tempe plain are a variety of features that appear structurally controlled, along an orientation of N60 deg E; comprising low shields, irregular hills that may be silicic domes, and possible composite cones. The Tempe/Snake River match is held to be the first in which direct comparison can be made between Martian and terrestrial geologic-geomorphic features without encountering problems of scale.

Plescia, J. B.↗
NASA NTRS1981

The topography of Ganymede's grooved terrain

Using the technique of photoclinometry, topographic profiles across areas of grooved terrain and several other features on Ganymede have been constructed. The grooved terrain examined consists of subparallel grooves spaced 3-10 km apart. Topographic amplitudes are typically 300-400 m, with a maximum of about 700 m. Slopes are very gentle and tend to be primarily concave upward. Very few major positive relief features exist on Ganymede. The most important of these is a broad, gently sloping dome-shaped feature 260 km in diameter and over 2 km high.

Squyres, S. W.↗
NASA NTRS1981

Viscous relaxation of impact craters on icy planetary surfaces - Determination of viscosity variation with depth

Spacecraft images show that the icy Galilean satellites have surfaces with very low topographic relief. Impact craters on Ganymede and Callisto are anomalously shallow and are characterized by sharp well-defined rims and domed floors. These morphological characteristics can be explained by viscous relaxation of topography on an icy crust in which the viscosity is uniform or decreases with depth. Under these conditions, large craters relax more rapidly than small craters, therefore explaining a possible underabundance of large craters. Viscous relaxation on an icy crust that is thin compared to the crater diameter or on a thick icy crust in which viscosity increases with depth could not produce this crater morphology and would result in the more rapid relaxation of small craters rather than large craters. The results of this study suggest that more detailed analysis of relaxing impact crater morphology may resolve the rate of viscosity decrease with depth and so provide evidence on the interior thermal evolution of icy planetary bodies.

Parmentier, E. M.↗