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At least 1,783 records · Page 99
All sourcesNASA NTRSDOE OSTI
NASA NTRS1972

Core sample depth relationships - Apollo 14 and 15.

The depth relationships for the Apollo 14 and 15 core tubes and the Apollo 15 drill core are presented, as determined from laboratory simulation studies. Sample at a depth of 40 cm in the Apollo 14 double core tube (virtually the same as the Apollo 12 tubes) represents material from a depth of approximately 58 cm in the lunar surface. The new design of the Apollo 15 core tube results in much less sample disturbance and the depth relationship is practically one-to-one, with sample recovery approaching 100%. The depth relationship for the drill core is also probably close to one-to-one, and its recovery ratio was also 100%.

Carrier, W. D., III↗
NASA NTRS1973

A comparison of two transient methods of measuring thermal conductivity of particulate samples.

A comparison is made of the line source (LS) method and the differential line source (DLS) method of measuring thermal conductivity of particulate materials in vacuum. The DLS method requires more instrumentation in the measuring circuitry (an additional amplifier and a differentiating circuit), but since it does not require a stable temperature to initiate a test, it does not need a sample temperature control system. DLS tests can be taken as the temperature in the samples is rising from liquid nitrogen temperature to room temperature. This eliminates the practice of extrapolating thermal conductivity over this large temperature range. Also, the advantages of reduced test time, data reduction time, and small sample temperature rise enable the experimenter to take about 7-12 DLS tests in the time of 2 LS tests. Test data from the two methods agree very well.

Scott, R. W.↗
NASA NTRS1974

Extendible probe for atmosphere sampling

Sampling probe is extended through small plug in heat shield by loaded bellows to sample planetary atmosphere for compositional analysis and total pressure during entry of space probe. Assembly prevents contamination of sample by gases from pyrotechnic device and serves as sealed plenum for atmospheric pressure sensor.

Jones, W. J.↗
NASA NTRS1973

Preliminary examination of lunar samples

An analysis of the lunar samples returned by Apollo 17 was conducted to determine the petrographic characteristics. A table listing all the rocks returned by Apollo 17 by sample number, weight, and rock type is presented. Photographs of lunar samples are included to show the variety of rocks returned. Lunar soils were collected to aid in characterizing the four major photogeologic units determined by preflight studies. Tables are developed to show grain size and grain type for the lunar soils. Radiographs of the drive tubes are interpreted to show the formations existing at various depths below the lunar surface.

Source record↗
NASA NTRS1974

Development study of the X-ray scattering properties of a group of optically polished flat samples

Four optically polished flat samples were tested at wavelengths of 8.34 A, 13.3 A, and 44 A and 0.5 deg, 0.92 deg, 1.5 deg, 2.0 deg and 4.0 deg angle of incidence. The four samples were also tested at 8.34 A and 0.92 deg angle of incidence for three additional angular orientations about an axis normal to the sample surface: 45 deg, 90 deg and 180 deg from the 0 deg position. The tests indicate that the scattering was greater at 44 A than at 13.3 A and 8.34 A. The orientation tests indicated that no great irregularities were present.

Froechtenigt, J. F.↗
NASA NTRS1973

Preparation of ultra small samples for optical and microprobe analysis

This paper describes a simple but satisfactory new method for the preparation of tiny, varied and specialized specimens for electron or ion-microprobe analysis developed over the past five years. Microtektites, individual chondrules, single grains, blebs from lunar samples and meteoritic minerals have been prepared by this technique. A description of the preparation of these usually difficult samples from the initial mounting through the various polishing steps to their final polish is presented in detail. The procedures used to prevent any contamination of these specimens by the polishing agents and to prevent cross contamination to the other samples used for geochronology studies are presented.

Inman, C. S.↗
NASA NTRS1973

Armalcolite and genetically associated opaque minerals in the lunar samples

A comprehensive electron microprobe study of armalcolite in samples from five Apollo sites (11-16), together with analytical data previously reported from Apollo 17 and Luna 20 show that three distinct compositional types of armacolite are present in the lunar samples. These types are classified as armalcolite, Cr-Zr-Ca-armalcolite and Zr-armalcolite. The Zr-free armalcolites are typical of high-Ti mare basalts whereas the Zr-rich armalcolites are typical of non-mare high alumina basalts. The latter armalcolites are in complete oxide intergrowths (baddeleyite, zirconolite, rutile, ilmenite, and chromite) and are in contrast to the Zr-free armalcolites which are commonly only associated with ilmenite. Subsolidus decomposition of armalcolite to an iron and Mg-rich rutile + ilmenite-geikielite, and the solid state formation of armalcolite from magnesium-ilmenite + niobian-rutile are described for the first time in the lunar samples.

Haggerty, S. E.↗
NASA NTRS1973

Elemental abundances of Apollo 16 samples

Results are presented for the multielement analysis of samples of lunar soil (60501 and 64501), igneous rock (60315), and the light portion of breccia 60017. A mixing model for soil compositions has been proposed consisting of linear combinations of the KREEP basalt 60315 and the anorthositic gabbroic sample 60017. A comparison of trace elements in lunar soils from different missions indicates the marked depletion of the LIL elements in the Apollo 16 samples.

Morrison, G. H.↗
NASA NTRS1973

Total carbon contents of Apollo 15 and 16 lunar samples

The total carbon contents in Apollo 15 fines range from 29 to 170 micrograms/g. Fines from Apollo 16 range from 65 to 280 micrograms/g. These samples are similar to those from Apollo 11, 12, and 14, with dark colored fines generally containing more carbon than lighter fines. Sample 61221 (light colored fines) is anomalously high with 100 micrograms/g total carbon. Correlations between total carbon content and sample collection station for each mission are evident. Basalts from Apollo 15 have less than 27 micrograms/g total carbon. Anorthositic rocks from Apollo 15 and 16 have less than 20 micrograms/g total carbon. Breccias show complex and variable carbon distributions.

Moore, C. B.↗
NASA NTRS1973

U-Th-Pb systematics of some Apollo 16 lunar samples

U, Th, and Pb concentrations and lead isotopic compositions of Apollo 16 samples are interpreted as follows: (1) an early period of lunar differentiation of either global or regional scale occurred about 4.47 b.y. ago; (2) the Imbrian impact event affected many Apollo 16 samples about 3.99 b.y. ago; (3) some Apollo 16 metaclastic rocks and breccias contain a large amount of KREEP-like material; (4) lead produced in the early history of the moon has been concentrated in lunar highland soils yielding high Pb-207/Pb-206 ratios corresponding to apparent ages of more than 4.8 b.y.; and (5) South Ray Crater soils reflect the approximately 2-b.y.-old event previously proposed for the Apollo 12 and 14 samples.

Nunes, P. D.↗
NASA NTRS1973

Interaction of gases with lunar materials - Apollo 12, 14, and 16 samples

Surface properties of lunar fines samples from the Apollo 12, 14, and 16 missions have been investigated by studying the adsorption of nitrogen, argon, oxygen, carbon monoxide (all at 77 K), and water vapor (at 20 or 22 C) on the samples. Initially the samples were all nonporous and had a uniformly low specific surface area (0.3 to 0.6 sq m/g). Water interacts strongly with the surface of lunar fines, chemisorbing at low pressures followed by a massive adsorption at high pressures. Nitrogen adsorption measurements after the interaction with water showed that the surface properties had undergone a severe alteration as a result of the attack by water vapor. This alteration consisted of a marked increase in the specific surface area and the creation of a pore system. The results are interpreted on the basis of a penetration of water into the damage tracks.

Holmes, H. F.↗
NASA NTRS1974

Mathematical estimation of the level of microbial contamination on spacecraft surfaces by volumetric air sampling

Microbiological sampling methods presently used for enumeration of microorganisms on spacecraft surfaces require contact with easily damaged components. Estimation of viable particles on surfaces using air sampling methods in conjunction with a mathematical model would be desirable. Parameters necessary for the mathematical model are the effect of angled surfaces on viable particle collection and the number of viable cells per viable particle. Deposition of viable particles on angled surfaces closely followed a cosine function, and the number of viable cells per viable particle was consistent with a Poisson distribution. Other parameters considered by the mathematical model included deposition rate and fractional removal per unit time. A close nonlinear correlation between volumetric air sampling and airborne fallout on surfaces was established with all fallout data points falling within the 95% confidence limits as determined by the mathematical model.

Oxborrow, G. S.↗
NASA NTRS1974

Selection of sampling rate for digital control of aircrafts

The considerations in selecting the sample rates for digital control of aircrafts are identified and evaluated using the optimal discrete method. A high performance aircraft model which includes a bending mode and wind gusts was studied. The following factors which influence the selection of the sampling rates were identified: (1) the time and roughness response to control inputs; (2) the response to external disturbances; and (3) the sensitivity to variations of parameters. It was found that the time response to a control input and the response to external disturbances limit the selection of the sampling rate. The optimal discrete regulator, the steady state Kalman filter, and the mean response to external disturbances are calculated.

Katz, P.↗
NASA NTRS1974

Content of lithium, beryllium, boron, and titanium, and the isotopic composition of lithium, boron, and magnesium in Luna 16 regolith sample

The abundance of the following elements in the L 16-19 No. 118 regolith sample, zone V was determined by isotopic dilution using a mass spectrometer equipped with a scattering ion source: Li -- 9.8, Be -- 1.2, Be -- 2.6, and Ti -- 1.92 percent. For comparison, these same elements were measured in samples of surface material returned by Apollo 11, Apollo 12, and Apollo 14, and in the terrestrial reference standard diabase W-1. The content of Li, Be, and B in the Luna 16 sample is nearly the same as in the Apollo 11 surface material. The surface material returned by Apollo 12 and Apollo 14 contains two to four times more of these elements. However, the abundance ratios of Li, Be, and B are remarkably similar in the surface materials from the four different lunar regions. With respect to basaltic achondrites and especially with respect to chondrites, the lunar basalts are enriched in Li, Be, and B up to 100 times.

Eugster, O.↗
NASA NTRS1975

Gas sampling method for determining pollutant concentrations in the flame zone of two swirl-can combustor modules

A gas sampling probe and traversing mechanism were developed to obtain detailed measurements of gaseous pollutant concentrations in the primary and mixing regions of combustors in order to better understand how pollutants are formed. The gas sampling probe was actuated by a three-degree-of-freedom traversing mechanism and the samples obtained were analyzed by an on-line gas analysis system. The pollutants in the flame zone of two different swirl-can combustor modules were measured at an inlet-air temperature of 590 K, pressure of 6 atmospheres, and reference velocities of 23 and 30 meters per second at a fuel-air ratio of 0.02. Typical results show large spatial gradients in the gaseous pollutant concentration close to the swirl-can module. Average concentrations of unburned hydrocarbons and carbon monoxide decrease rapidly in the downstream wake regions of each module. By careful and detailed probing, the effect of various module design features on pollutant formation can be assessed. The techniques presently developed seem adequate to obtain the desired information.

Duerr, R. A.↗
NASA NTRS1975

Automated Mars surface sample return mission concepts for achievement of essential scientific objectives

Mission concepts were investigated for automated return to Earth of a Mars surface sample adequate for detailed analyses in scientific laboratories. The minimum sample mass sufficient to meet scientific requirements was determined. Types of materials and supporting measurements for essential analyses are reported. A baseline trajectory profile was selected for its low energy requirements and relatively simple implementation, and trajectory profile design data were developed for 1979 and 1981 launch opportunities. Efficient spacecraft systems were conceived by utilizing existing technology where possible. Systems concepts emphasized the 1979 launch opportunity, and the applicability of results to other opportunities was assessed. It was shown that the baseline missions (return through Mars parking orbit) and some comparison missions (return after sample transfer in Mars orbit) can be accomplished by using a single Titan III E/Centaur as the launch vehicle. All missions investigated can be accomplished by use of Space Shuttle/Centaur vehicles.

Weaver, W. L.↗
NASA NTRS1975

Mars sample return by orbital rendezvous

The return of Mars surface samples by the orbital rendezvous mode would require smaller, lighter vehicles than the direct return mode and would limit the exposure of the earth return systems to possible contamination by Martian biota. The reference mission considered would use a single Titan IIIE/Centaur launch vehicle, carry a 1 kg sample, and be launched in late 1981. The spacecraft would consist of an orbiter, a Mars lander, a Mars ascent vehicle, an earth return vehicle, and an earth entry capsule. The Mars ascent vehicle is the only all-new vehicle required, the others being derived from Viking and other programs. A key consideration is the feasibility of automatic rendezvous and sample transfer between the ascent vehicle and orbiter in Mars orbit. The maneuvers required and the maneuver algorithm developed in a NASA feasibility study are described in detail. The possibility of international cooperation on a Mars orbital rendezvous mission is discussed.

Moore, J. W.↗
NASA NTRS1974

Possible magnetic effects due to fine particle metal and intergrown phases in lunar samples

The characteristics and forms of existence for alpha iron and gamma iron are considered along with experimental observations concerning the alpha to gamma iron transformation. Attention is given to iron-copper precipitation alloys, the origin of rotational hysteresis in lunar samples, questions of paleointensity, and results obtained in the study of lunar samples. It is pointed out that the presence of gamma iron as a significant component in lunar fines and breccia samples would make it necessary to include the gamma iron component in an interpretation of the magnetic susceptibility-temperature curves.

Wasilewski, P.↗