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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 181 records · Page 10
All sourcesNASA NTRSDOE OSTI
NASA NTRS1974

Epitaxial growth of 6H silicon carbide in the temperature range 1320 C to 1390 C

High-quality epitaxial layers of 6H SiC have been grown on 6H SiC substrates with the grown direction perpendicular to the crystal c-axis. The growth was by chemical vapor deposition from methyltrichlorosilane (CH3SiCl3) in hydrogen at temperatures in the range of 1320 to 1390 C. Epitaxial layers up to 80 microns thick were grown at rates of 0.4 microns/min. Attempts at growth on the (0001) plane of 6H SiC substrates under similar conditions resulted in polycrystalline cubic SiC layers. Optical and X-ray diffraction techniques were used to characterize the grown layers.

Will, H. A.↗
NASA NTRS1975

Friction and wear of tin and tin alloys from minus 100 C to 150 C

Sliding friction experiments were conducted with an iron (110) single-crystal pin sliding on single and polycrystalline tin and tin alloys. Specimens were examined at various ambient temperatures from -100 to 150 C. Applied loads varied from 1 to 50 grams, and sliding velocity was constant at 0.7 mm/min. Results indicate that the crystal transformation of tin influences the friction coefficient. Friction was higher for the diamond structure (gray tin) than it was for the body-centered tetragonal structure (white tin). Bismuth arrested the crystal transformation, which resulted in constant friction over the temperature range -100 to 150 C. Both copper and aluminum enhanced the kinetics of transformation, with aluminum producing a nearly twofold change in friction with the crystal transformation.

Buckley, D. H.↗
NASA NTRS1976

GEOS-C C-band transponder prelaunch calibration and test data

The delay characteristics and spacecraft telemetry housekeeping data for the GEOS-C C-Band transponders are presented. The data are presented in graphical form to provide a convenient method for computing radar range measurement corrections as a function of signal strength at the transponder and spacecraft environment. The data are also presented in tabular form along with the mathematical models used to derive the curves. Also included are a list of the operating characteristics of each transponder and a description of the calibration test equipment set-up.

Selser, A. R.↗
NASA NTRS1982

Tribological properties at 25 C of seven polyimide films bonded to 440 C high-temperature stainless steel

The tribological properties of seven polyimide films applied to 440 C high temperature stainless steel substrates were studied at 25 C with a pin-on-disk type of friction and were apparatus. The polyimides fell into two groups according to friction and wear properties. Group I polyimides had slightly lower friction but much higher wear than group II polyimides. The wear mechanism was predominately adhesion, but the wear particles were larger for group I polyimides. For most of the polyimides the transfer films consisted of clumps of compacted wear particles. One polyimide composition produced a very thin transfer film that sheared plastically in the contact area.

Fusaro, R. L.↗
NASA NTRS1983

Shuttle Imaging Radar-C (SIR-C): Executive summary

The scientific and technological objectives of the Shuttle Imaging Radar-C (SIR-C) Project are reviewed. Information regarding the implementation philosophy and approach, and the relationship of the project to the overall SIR program is also provided.

Source record↗
NASA NTRS1986

Measurements of electron attachment lineshapes and cross sections at ultralow electron energies for c-C6F10, c-C6F12, C8F16 and 1,1,2-C2Cl3F3

Electron attachment cross sections are reported in the electron energy range 0-160 meV and at energy resolutions of 4.5-7.5 meV (FWHM) for the molecules c-C6F10 (perfluorocyclohexene), c-C6F12 (perfluoro-1,2-dimethylcyclobutane), C8F16 (perfluoro-1,3-dimethylcyclohexane) and 1,1,2-C2Cl3F3 (1,1,2-trichlorotrifluoroethane). Use is made of the Kr photoionization technique, and measured attachment lineshapes are converted to cross sections by normalization through attachment rate constants. Comparisons are made with attachment cross sections derived from swarm-measured rate constants. Similar to previous results in eight other molecules, the present four molecules exhibit resolution-limited onsets at a threshold consistent with an s-wave attachment behavior and with a neutral-negative-ion curve crossing at zero energy.

Alajajian, S. H.↗
NASA NTRS1986

Behavior of insoluble particles during parabolic flight solidification processing of Fe-C-Si and Fe-C-V alloys

In a high-g rapid solidification environment, Fe-base alloy insoluble particles at the solidification interface may be pushed ahead of the interface or may be trapped in the solid, depending on the correlation of various interface energies, the solidification rates, and the Stokes force; particle agglomeration due to buoyancy-driven convection further complicates the problem. Attention is presently given to results obtained for directionally solidified Fe-C-Si and Fe-C-V alloys during parabolic low-g flight and ground experiments. In these systems, graphite and vanadium carbide can be considered to be the insoluble particles.

Stefanescu, D. M.↗
NASA NTRS1990

Corrections regarding the Lellouch et al. (1989) analysis of Mars atmospheric C-12O and C-13O spectra

Lellouch et al. (1989) obtained atmospheric CO mixing ratios from Martian C-12O and C-13O microwave spectra that were 3-5 times greater than the Kaplan et al. (1969) IR measurememts; they also inferred a factor-of-2 increase in atmospheric CO abundance between September, 1986 and January, 1987. A reanalysis has been conducted of the Lellouch material, and more detailed treatment of the radiative transfer analysis indicates that its observations are consistent with the Kaplan CO volume mixing ratio determination. It is also ascertained that the Lellouch atmospheric temperature profiles are in error, with no evidence being found for the extreme temperature inversions inferred for the lowest 5 km of the Martian atmosphere.

Clancy, R. Todd↗
NASA NTRS1990

The anomalous 3.43 and 3.53 micron emission features toward HD 97048 and Elias 1 - C-C vibrational modes of polycyclic aromatic hydrocarbons?

The 5-8 micron spectra obtained toward the two protostellar sources, HD 97048 and Elias 1 exhibit strong anomalous emission features at 3.43 and 3.53 microns. Combining these results with earlier data established that the emission in the general IR features is extended on at least a 20-arcsec scale. In view of the high energy density in the emission zone, as well as the apparent correspondence of the anomalous 3.43 and 3.53 micron features with weak emission shoulders associated with the general family of IR emission bands, an explanation for these observations in terms of C-C overtones and combination tones of large or dehydrogenated polycyclic aromatic hydrocarbons is judged to be provisionally suitable.

Schutte, W. A.↗
NASA NTRS1988

Bisannelation with a benzo(1,2-c:4,5-c-prime) difuran equivalent - A new route to linear acene derivatives

It was observed that the base peak in the mass spectra of all the Diels-Alder bis adducts of anthracene diendoxide as well as of its tetrahydro derivative appear at m/e 158, corresponding to the radical cation of benzo(1,2-c:4,5-c-prime) difuran (BDF). This paper describes a synthetic equivalent of BDF and demonstrates its utility for obtaining linear acene derivatives.

Luo, Jihmei↗
NASA NTRS1991

The computation of C-C and N-N bond dissociation energies for singly, doubly, and triply bonded systems

The bond dissociation energies (De) of C2H2, C2H4, C2H6, N2, N2H2, and N2H4 are studied at various levels of correlation treatment. The convergence of De with respect to the one-particle basis is studied at the single-reference modified coupled-pair-functional (MCPF)level. At all levels of correlation treatment, the errors in the bond dissociation energies increase with the degree of multiple bond character. The multireference configuration-interaction (MRCI) De values, corrected for an estimate of higher excitations, are in excellent agreement with those determined using the size-extensive averaged-coupled-pair-functional (ACPF) method. The full-valence complete-active-space self-consistent-field (CASSCF)/MRCI calculations are reproduced very well by MRCI calculations based on a CASSCF calculation that includes in the active space only those electrons involved in the C-C or N-N bonds.

Langhoff, Stephen R.↗
NASA NTRS1989

The computation of C-C and N-N bond dissociation energies for singly, doubly, and triply bonded systems

The bond dissociation energies (D sub e) of C2H2, C2H4, C2H6, N2, N2H2, and N2H4 are studied at various levels of correlation treatment. The convergence of D sub e with respect to the one particle basis is studied at the single reference modified coupled-pair functional (MCPF) level. At all levels of correlation treatment, the errors in the bond dissociation energies increase with the degree of multiple bond character. The multireference configuration interaction (MRCI) D sub e values, corrected for an estimate of higher excitations, are in excellent agreement with those determined using the size extensive averaged coupled pair functional (ACPF) method. It was found that the full valence complete active space self consistent field (CASSCF)/MRCI calculations are reproduced very well by MRCI calculations based on a CASSCF calculation that includes in the active space only those electrons involved in the C-C or N-N bonds. To achieve chemical accuracy (1 kcal/mole) for the D sub e values of the doubly bonded species C2H4 and N2H2 requires one particle basis sets including up through h angular momentum functions (l = 5) and a multireference treatment of electron correlation: still higher levels of calculation are required to achieve chemical accuracy for the triply bonded species C2H2 and N2.

Langhoff, Stephen R.↗
NASA NTRS1992

Dipole moments and transition probabilities of the i 3Pi sub g-b 3Sigma(+) sub u, c 3Pi sub u-a 3Sigma(+) sub g, and i 3Pi sub g-c 3Pi sub u systems of molecular hydrogen

Bonn-Oppenheimer-based ab initio calculations of dipole moments from the i 3Pi sub g-b 3Sigma(+) sub u, c 3Pi sub u-a 3Sigma(+) sub g, and i 3Pi sub g-c 3Pi sub u transitions of H2 have been conducted, to yield a tabulation of the dipole transition probabilities and Franck-Condon factors. These factors are given for transitions originating in the lowest vibrational level of the ground X 1Sigma(+) sub g state.

Guberman, Steven L.↗
NASA NTRS1992

Tribological behavior of 440C martensitic stainless steel from -184 C to 750 C

Characterization of the coefficient of friction and wear rate of 440C stainless steel is needed to understand the effects of frictional heating in the bearings of the High Pressure Oxygen Turbopump of the Space Shuttle Main Engine. The coefficient of friction and wear rate have been measured over a range of temperature varying from liquid oxygen temperature (-184 C) to 750 C. The normal load has also been varied resulting in a variation of Hertzian stress from 0.915 to 3.660 GPa while the surface velocity has been varied from 0.5 to 2.0 m/s.

Slifka, A. J.↗
NASA NTRS1993

Mission planning for Shuttle Imaging Radar-C (SIR-C) with a real-time interactive planning software

The Shuttle Imaging Radar-C (SIR-C) mission will operate from the payload bay of the space shuttle for 8 days, gathering Synthetic Aperture Radar (SAR) data over specific sites on the Earth. The short duration of the mission and the requirement for realtime planning offer challenges in mission planning and in the design of the Planning and Analysis Subsystem (PAS). The PAS generates shuttle ephemerides and mission planning data and provides an interactive real-time tool for quick mission replanning. It offers a multi-user and multiprocessing environment, and it is able to keep multiple versions of the mission timeline data while maintaining data integrity and security. Its flexible design allows one software to provide different menu options based on the user's operational function, and makes it easy to tailor the software for other Earth orbiting missions.

Potts, Su K.↗
NASA NTRS1999

Die Attachment for -120 C to +20 C Thermal Cycling of Microelectronics for Future Mars Rovers: An Overview

Active thermal control for electronics on Mars Rovers imposes a serious penalty in weight, volume, power consumption, and reliability. Thus, we propose that thermal control be eliminated for future Rovers. From a functional standpoint there is no reason that the electronics could not operate over the entire temperature range of the Martian environment, which can vary from a low of approximately equal -90 C to a high of approximately equal +20 C during the Martian night and day. The upper end of this range is well within that for conventional electronics. Although the lower end is considerably below that for which conventional--even high-reliability electronics is designed or tested, it is well established that electronic devices can operate to such low temperatures. The primary concern is reliability of the overall electronic system, especially in regard to the numerous daily temperature cycles that it would experience over the duration of a mission on Mars. Accordingly, key reliability issues have been identified for elimination of thermal control on future Mars Rovers. One of these is attachment of semiconductor die onto substrates and into packages. Die attachment is critical since it forms a mechanical, thermal and electrical interface between the electronic device and the substrate or package. This paper summarizes our initial investigation of existing information related to this issue, in order to form an opinion whether die attachment techniques exist, or could be developed with reasonable effort, to withstand the Mars thermal environment for a mission duration of approximately I year. Our conclusion, from a review of literature and personal contacts. is that die attachment can be made sufficiently reliable to satisfy the requirements of future Mars Rovers. Moreover, it appears that there are several possible techniques from which to choose and that the requirements could be met by judicious selection from existing methods using hard solders, soft solders, or organic adhesives. Thus from the standpoint of die attachment. it appears feasible to eliminate thermal control for Rover electronics. We recommend that this be further investigated and verified for the specific hardware and thermal conditions appropriate to Mars Rovers.

Kirschman, Randall K.↗
NASA NTRS2008

Bonding and Integration of C-C Composite to Cu-Clad-Molybdenum for Thermal Management Applications

Two- and three-dimensional carbon-carbon composites with either resin-derived matrix or CVI matrix were joined to Cu-clad-Mo using active Ag-Cu braze alloys for thermal management applications. The joint microstructure and composition were examined using Field-Emission Scanning Electron Microscopy and Energy-Dispersive Spectroscopy, and the joint hardness was characterized using the Knoop microhardness testing. Observations on the infiltration of the composite with molten braze, dissolution of metal substrate, and solute segregation at the C-C surface have been discussed. The thermal response of the integrated assembly is also briefly discussed.

Asthana, R.↗