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At least 451 records · Page 25

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NASA NTRS1987

Computer simulations of 10-km-diameter asteroid impacts into oceanic and continental sites: Preliminary results on atmospheric passage, cratering and ejecta dynamics

A series of analytical calculations of large scale cratering events for both oceanic and continental sites were made in order to examine their effects on the target media and atmosphere. The first analytical studies that were completed consists of computer simulations of the dynamics of: (1) the passage of a 10 km diameter asteroid moving at 20 km/sec through the Earth's atmosphere, and (2) the impact cratering events in both oceanic and continental environments. Calculation of the dynamics associated with the passage of the asteroid through the atmosphere showed strong effects on the surrounding air mass. The calculations of the impact cratering events showed equally dramatic effects on the oceanic and continental environments. These effects are briefly discussed.

Roddy, D. J.↗

NASA NTRS1987

Quasi-static shape adjustment of a 15 meter diameter space antenna

A 15 meter diameter Hoop-Column antenna has been analyzed and tested to study shape adjustment of the reflector surface. The Hoop-Column antenna concept employs pretensioned cables and mesh to produce a paraboloidal reflector surface. Fabrication errors and thermal distortions may significantly reduce surface accuracy and consequently degrade electromagnetic performance. Thus, the ability to adjust the surface shape is desirable. The shape adjustment algorithm consisted of finite element and least squares error analyses to minimize the surface distortions. Experimental results verified the analysis. Application of the procedure resulted in a reduction of surface error by 38 percent. Quasi-static shape adjustment has the potential for on-orbit compensation for a variety of surface shape distortions.

Belvin, W. Keith↗

NASA NTRS1987

Wind tunnel tests on a one-foot diameter SR-7L propfan model

Wind tunnel tests have been conducted on a one-foot diameter model of the SR-7L propfan in the Langley 16-Foot and 4 x 7 Meter Wind Tunnels as part of the Propfan Test Assessment (PTA) Program. The model propfan was sized to be used on a 1/9-scale model of the PTA testbed aircraft. The model propeller was tested in isolation and wing-mounted on the aircraft configuration at various Mach numbers and blade pitch angles. Agreement between data obtained from these tests and data from Hamilton Standard validate that the 1/9-scale propeller accurately simulates the aerodynamics of the SR-7L propfan. Predictions from an analytical computer program are presented and show good agreement with the experimental data.

Aljabri, Abdullah S.↗

NASA NTRS1987

Isophotal diameters of galaxies at high redshifts

New ultraviolet observations and archival spectra are presented for the bright disk of the galaxy NGC 4736 to derive the ultraviolet surface brightness profile. This is used to predict the appearance of such a galaxy at high redshift. The profiles in red light of 100 galaxies determined by S. Kent (1984) are used with assumed ultraviolet spectra to predict the isophotal diameters of these galaxies as a function of redshift. The results show that, for ground-based imagery, normal spiral galaxies should be resolvable to the largest redshifts (z roughly 1). For space-based imagery, much smaller but brighter galactic disks characterized by extensive star formation will be those resolved at the highest redshifts (z roughly 2.5).

Weedman, Daniel W.↗

NASA NTRS1987

Influence of Reynolds number on forebody side forces for 3.5-diameter tangent-ogive bodies

Vortex asymmetries can arise on aircraft and missile forebodies at high angles of attack and have proven difficult to simulate in the wind tunnel because of a large array of parameters that can influence the test results. One of the most important of these parameters is Reynolds number. The current report compares, for tangent-ogive forebodies with fineness ratios of 3.5, flow patterns from oil-flow photographs to features in pressure distributions. The pressure data base is then used to illustrate the development of the sectional side force coefficient along both the tangent-ogive nose and an attached cylindrical afterbody for Reynolds numbers of 0.2, 0.8 and 3.8 million, based on maximum diameter, and angles of attack of 40, 50 and 60 deg. General commments concerning the effects of Reynolds number are presented, as well as an analysis of the effects of Reynolds number on the sectional side force coefficient near and at the apex of the pointed body. All data presented are for freestream Mach numbers on the order of 0.25.

Hall, Robert M.↗

NASA NTRS1987

Cylindrical surface profile and diameter measuring tool and method

A tool is shown having a cross beam assembly made of beams joined by a center box structure. The assembly is adapted to be mounted by brackets to the outer end of a cylindrical case. The center box structure has a vertical shaft rotatably mounted therein and extending beneath the assembly. Secured to the vertical shaft is a radius arm which is adapted to rotate with the shaft. On the longer end of the radius arm is a measuring tip which contacts the cylindrical surface to be measured and which provides an electric signal representing the radius of the cylindrical surface from the center of rotation of the radius arm. An electric servomotor rotates the vertical shaft and an electronic resolver provides an electric signal representing the angle of rotation of the shaft. The electric signals are provided to a computer station which has software for its computer to calculate and print out the continuous circumference profile of the cylindrical surface, and give its true diameter and the deviations from the ideal circle.

Currie, James R.↗

NASA NTRS1988

Experiments for the determination of convective diffusion heat/mass transfer to burner rig test targets comparable in size to jet stream diameter

The application of a recently formulated vapor transport theory to predict deposition rates of corrosive salts from alkali-seeded combustion gases of a small-capacity, high-velocity, atmospheric-pressure burner rig was hampered by the relatively large dimensions of the cylindrical deposit collector compared to the diameter of the combustion gas stream. The relative dimensions lead to a highly nonadiabatic combustion gas flow around the collector and necessitate two series of experiments. In the first series, mass transfer coefficients are determined by utilizing the naphthalene sublimation technique. The second series of experiments determines the dilution effect on the sodium species concentrations due to the entrainment of ambient air. This second series involves the measurement of the temperature variation along the surface of the collector under steady state conditions. Vapor deposition rates are determined exploiting this information and the results are found to compare favorably with experimentally obtained rates.

Santoro, G. J.↗

NASA NTRS1988

The effect of front-to-rear propeller spacing on the interaction noise at cruise conditions of a model counterrotation propeller having a reduced diameter aft propeller

The effect of forward-to-aft propeller spacing on the interaction noise of a counterrotation propeller with reduced aft diameter was measured at cruise conditions. In general, the tones at 100 percent speed decreased from close to nominal spacing as expected from a wake decay model. However, when the spacing was further increased to the far position, the noise did not decrease as expected and in some cases increased. The behavior at the far spacing was attributed to changing forward propeller performance, which produced larger wakes. The results of this experiment indicate that simple wake decay model is sufficient to describe the behavior of the interaction noise only if the aerodynamic coupling of the two propellers does not change with spacing. If significant coupling occurs such that the loading of the forward propeller is altered, the interaction noise does not necessarily decrease with larger forward-to-aft propeller spacing.

Dittmar, James H.↗

NASA NTRS1989

Structural and thermal response of 30 cm diameter ion thruster optics

Tabular and graphical data are presented which are intended for use in calibrating and validating structural and thermal models of ion thruster optics. A 30 cm diameter, two electrode, mercury ion thruster was operated using two different electrode assembly designs. With no beam extraction, the transient and steady state temperature profiles and center electrode gaps were measured for three discharge powers. The data showed that the electrode mount design had little effect on the temperatures, but significantly impacted the motion of the electrode center. Equilibrium electrode gaps increased with one design and decreased with the other. Equilibrium displacements in excess of 0.5 mm and gap changes of 0.08 mm were measured at 450 W discharge power. Variations in equilibrium gaps were also found among assemblies of the same design. The presented data illustrate the necessity for high fidelity ion optics models and development of experimental techniques to allow their validation.

Macrae, G. S.↗

NASA NTRS1989

Structural and thermal response of 30 cm diameter ion thruster optics

This paper presents tabular and graphical data intended for use in calibrating and validating structural and thermal models of ion thruster optics. A 30-cm-diameter, two electrode, mercury ion thruster was operated using two different electrode assembly designs. With no beam extraction, the transient and steady state temperature profiles and center electrode gaps were measured for three discharge powers. The data showed that the electrode mount design had little effect on the temperatures, but significantly impacted the motion of the electrode center. Equilibrium electrode gaps increased with one design and decreased with the other. Equilibrium displacements in excess of 0.5 mm and gap changes of 0.08 mm were measured at 450 W discharge power. Variations in equilibrium gaps were also found among assemblies of the same design. The presented data illustrate the necessity for high fidelity ion optics models and development of experimental techniques to allow their validation.

Macrae, G.↗

NASA NTRS1989

The diameter, shape, albedo, and rotation of 47 Aglaja

Observations of the September 16, 1984 occultation of SAO 146599 by the C-type asteroid 47 Aglaja from 13 sites in the continental U.S. have yielded a diameter of 136.4 + or - 1.2 km, leading to the calculation of a rotational period of 13.2 + or - 0.01 hr. At the time of the occultation, the zero-phase-angle visual geometric albedo of the asteroid's phase was 0.071 + or - 0.002. It is suggested that a substantial portion of the object's mean brightness variation with ecliptic longitude is ascribable to albedo differences over its surface.

Millis, R. L.↗

NASA NTRS1989

A search for X-ray counterparts to small-diameter Galactic radio sources

By comparing observations obtained with the Einstein Observatory to the Molonglo catalog of small-diameter radio sources near the Galactic plane, the number of supernova remnants contained in the radio sample has been constrained. The one known remnant among the 47 sources falling in Einstein fields was easily detected and another candidate remnant (G274.7-2.8) was discovered. The latter object has properties consistent with that of either a young shell-like or composite remnant, although an identification as a radio-loud quasar cannot be excluded. Apart from cases in which very large absorbing column densities are appropriate, upper limits to the X-ray emission from the remainder of the sample places most of the objects outside of the ranges of parameters that characterize the Galactic remnant population.

Helfand, D. J.↗

NASA NTRS1989

Asteroid magnitudes, UBV colors, and IRAS albedos and diameters

This paper lists absolute magnitudes and slope parameters for known asteroids numbered through 3318. The values presented are those used in reducing asteroid IR flux data obtained with the IRAS. U-B colors are given for 938 asteroids, and B-V colors are given for 945 asteroids. The IRAS albedos and diameters are tabulated for 1790 asteroids.

Tedesco, Edward F.↗

NASA NTRS1990

Preliminary design considerations for 10 to 40 meter-diameter precision truss reflectors

A simplified preliminary design capability for erectable precision segmented reflectors is presented. This design capability permits a rapid assessment of a wide range of reflector parameters as well as new structural concepts and materials. The preliminary design approach was applied to a range of precision reflectors from 10 meters to 100 meters in diameter while considering standard design drivers. The design drivers considered were: weight, fundamental frequency, launch packaging volume, part count, and on-orbit assembly time. For the range of parameters considered, on-orbit assembly time was identified as the major design driver. A family of modular panels is introduced which can significantly reduce the number of reflector parts and the on-orbit assembly time.

Mikulas, Martin M., Jr.↗

NASA NTRS1989

Effects of cardiac phase on diameter measurements from coronary cineangiograms

The measurement variability of end-diastolic frames is compared with frames taken from the other portions of the cardiac cycle. Two computer measurements, average diameter and minimum, are obtained for every frame of two complete cardiac cycles in angiograms of 20 subjects. Six schemes for sampling frames in various portions of the cardiac cycle are defined and the standard deviation is calculated for pairs of measurements from each scheme. The results suggest that the best strategy for frame selection is to use sequential frames in end-diastole. However, it is noted that if random samples are taken anywhere in the cardiac cycle instead of sequentially in end-diastole, the variability of two vessel edge measures changes from 4.9 percent to 6.3 percent, which is considered to be a small penalty.

Selzer, Robert H.↗

NASA NTRS1991

Efficiency calibration of the DSS 13 34-meter diameter beam waveguide antenna at 8.45 and 32 GHz

Efficiency measurements at 8.45 and 32 GHz (X and Ka bands, respectively) were carried out on the new 34 m diameter beam waveguide antenna now in use at the NASA Goldstone Deep Space Communications Complex. The use of portable test packages enabled measurements at both the Cassegrain and beam waveguide focal points. Radio sources (quasars and Venus) were used as calibrators, and updated determinations of flux and source size correction were made during the period of the measurements. Gain and efficiency determinations as a function of elevation angle are presented, and the effects of the beam waveguide system and antenna structure are clearly seen. At the beam waveguide focus, an 8.45 GHz peak efficiency of 72.38 pct. was measured; at 32 GHz, 44.89 pct. was measured.

Slobin, S. D.↗

NASA NTRS1991

Aerothermodynamics of a 1.6-m-diameter sphere in hypersonic rarefied flow

Results of a numerical study using the direct simulation Monte Carlo (DSMC) method are presented for hypersonic rarefied flow about a 1.6-m-diameter sphere. The flow conditions considered are those experienced by a typical satellite in orbit or by a space vehicle during entry. The altitude range considered is that from 90 to 200 km, which encompasses the near continuum, transitional and free-molecular flow regimes. A freestream velocity of 7.5 km/s is assumed in the simulations. The results show that transitional effects are significant at all altitudes below 200 km, but at 200 km the flow about the sphere attains the free-molecular limit. Very little chemical activity is present above 120 km. Both the stagnation point heat transfer and the sphere drag approach their respective free molecule values at 200 km. Results highlight the thermal and chemical nonequilibrium nature of the flowfield. Nonequilibrium effects on the surface heating and body drag are also investigated.

Dogra, Virendra K.↗

NASA NTRS1990

Cryogenic surface distortion and hysteresis of a 50 cm diameter fused silica mirror cooled to 77 K

A 50 cm diameter, lightweight, Amersil TO8E, fused-natural-quartz mirror with a single arch cross section was tested at the NASA/Ames Research Center Cryogenic Optics Test Facility to measure cryogenic distortion and hysteresis. The mirror was cooled to 77 K in four serial tests and the mirror figure was measured with a phase-measuring interferometer. On the basis of the repeatability of room temperature and cryogenic optical measurements, it was determined that the Single Arch Mirror had no measurable hysteresis and displayed repeatable cryogenic distortion. The Cryogenic Optics Test Facility, optical and thermal test methods, test results, and measurement accuracy are described.

Young, Jeffrey A.↗