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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 631 records · Page 35
All sourcesNASA NTRSDOE OSTI
NASA NTRS1988

Crystallization of BaF2-ZnF2-YbF3-ThF4 glass

The phases and the rates of crystallization in a Ba-Zn-Yb-Th fluoride glass were studied using differential scanning calorimetry, XRD, and observational and chemical SEM analyses. The crystallizing phases that were identified included a BaYbTh fluoride, ZnF2, and YbF3. The BaYbTh fluoride crystallized first at about 450 C, and ZnF2, which was excluded from this phase, crystallized at its surfaces. At higher temperatures, the BaYbTh fluoride phase decomposed partially to BaThF6 and YbF3 phases.

Garcia, Roberto↗
NASA NTRS1988

Geometric angles in cyclic evolutions of a classical system

A perturbative method, using Lie transforms, is given for calculating the Hannay angle for slow, cyclic evolutions of a classical system, taking into account the finite rate of change of the Hamiltonian. The method is applied to the generalized harmonic oscillator. The classical Aharonov-Anandan angle is also calculated. The interpretational ambiguity in the definitions of geometrical angles is discussed.

Bhattacharjee, A.↗
NASA NTRS1989

The use of DFDR information in the analysis of a turbulence incident over Greenland

Digital flight data recorder (DFDR) tapes from commercial aircraft can provide useful information about the mesoscale environment of severe turbulence incidents. Air motion computations from these data and their errors are briefly described. An example of mesoscale meteorological information available from DFDR tapes is presented for a case of turbulence in mountain waves over the Greenland icecap.

Lester, Peter F.↗
NASA NTRS1990

LOX manifold tee analysis

A 4000 Hz vibration phenomena was observed during the test firings of several space shuttle main engines (SSME). Experimental studies of this phenomena suggest that the problem might be associated with vortex shedding from the vanes within the LOX tee manifold. The objective of this study was to determine the unsteady, 3-D flow associated with these vanes by computational methods to identify and better understand the 4000 Hz vibration phenomena. A flow solver, FDNS, for the turbulent conservation equations was validated for predicting high frequency vortex dynamics and used to predict 2-D and 3-D flows within the LOX tee. 4000 Hz excitation oscillations were predicted for some flows and the entire 3-D flow structure was predicted for LOX tee flow. The complexity of the flow was revealed by this analysis, and computational methods for predicting these high frequency oscillations in future engine systems were established.

Chen, Yen-Sen↗
NASA NTRS1990

Numerical investigation of the transient SSME fuel preburner combustor flowfield

A computational fluid dynamics (CFD) model with finite-rate reactions, FDNS2DR, has been developed to study the start transient of the Space Shuttle Main Engine Fuel Preburner (FPB) operation. This design tool can predict accurately the severe thermal gradients which are impressed upon the fuel preburner and turbine during the start transient. An axisymmetric configuration with a grid size of 68 x 45 is used to represent the FPB flowfield. The transient upstream boundary conditions are obtained from a one-dimensional Digital Transient Model simulation to better represent the actual operation. The results of the CFD calculation show temperature spikes near the FPB exit whose timing and magnitude agree well with those of the measured turbine inlet temperature data.

Wang, Ten-See↗
NASA NTRS1990

A unified Navier-Stokes flowfield and performance analysis of liquid rocket engines

To improve the current composite solutions in the design and analysis of liquid propulsive engines, a computational fluid dynamics model capable of calculating the nonreacting and reacting flows from the combustion chamber, through the nozzle to the external plume, was developed. The Space Shuttle Main Engine (SSME) fired at sea level, along with the flowfields of several other nozzles were investigated. The bell-shaped SSME nozzle was run at 100 percent power level at various flow conditions, the computed flow results and performance compared well with those of other standard codes and engine hot fire test data.

Wang, Ten-See↗
NASA NTRS1990

Cloud and surface textural features in polar regions

The study examines the textural signatures of clouds, ice-covered mountains, solid and broken sea ice and floes, and open water. The textural features are computed from sum and difference histogram and gray-level difference vector statistics defined at various pixel displacement distances derived from Landsat multispectral scanner data. Polar cloudiness, snow-covered mountainous regions, solid sea ice, glaciers, and open water have distinguishable texture features. This suggests that textural measures can be successfully applied to the detection of clouds over snow-covered mountains, an ability of considerable importance for the modeling of snow-melt runoff. However, broken stratocumulus cloud decks and thin cirrus over broken sea ice remain difficult to distinguish texturally. It is concluded that even with high spatial resolution imagery, it may not be possible to distinguish broken stratocumulus and thin clouds from sea ice in the marginal ice zone using the visible channel textural features alone.

Welch, Ronald M.↗
NASA NTRS1991

Jet Boost Pumps For The Space Shuttle Main Engine

Brief report proposes use of jet boost pumps in conjunction with main pumps supplying liquid hydrogen and liquid oxygen to main engine of Space Shuttle. Main part of pump has no moving parts. Benefits include increased reliability, simplified ducts, and decreased weight.

Meng, Sen Y.↗
NASA NTRS1990

Computation of Space Shuttle high-pressure cryogenic turbopump ball bearing two-phase coolant flow

A homogeneous two-phase fluid flow model, implemented in a three-dimensional Navier-Stokes solver using computational fluid dynamics methodology is described. The application of the model to the analysis of the pump-end bearing coolant flow of the high-pressure oxygen turbopump of the Space Shuttle main engine is studied. Results indicate large boiling zones and hot spots near the ball/race contact points. The extent of the phase change of the liquid oxygen coolant flow due to the frictional and viscous heat fluxes near the contact areas has been investigated for the given inlet conditions of the coolant.

Chen, Yen-Sen↗
NASA NTRS1990

Association reactions at low pressure. III - The C2H2(+)/C2H2 system

An ion cyclotron resonance mass spectrometer is used to examine the association reactions, C4H2(+) + C2H2 and C4H3(+) + C2H2, at pressures in the range of 8 x 10 to the -8 to 1 x 10 to the -4 Torr at 298 K. The association of C4H2(+) and C4H3(+) with C2H2 was found to exhibit classical behavior in the pressure range of 5 x 10 to the -8 Torr to 0.4 Torr. It is found that an efficient route via radiative association exists for unsaturated hydrocarbon cations to convert to aromatic structures in the presence of acetylene.

Anicich, Vincent G.↗
NASA NTRS1990

Neptune encounter - Guidance and control's finest hour

The Voyager 2 technology had to be stretched significantly to confront the challenges posed by the environment of Neptune. Little was known about Neptune's characteristics because of its great distance from the sun; and its reduced light levels required longer exposure time. Thus, it was necessary to reduce the spacecraft limit cycle; this was made more difficult by the trajectory selected, which caused high spacecraft-to-target rates (these rates dictated the use of image motion compensation). Another challenge faced by Voyager 2 was the need to perform all the required image motion compensation with a limited quantity of attitude control computer and command computer memory, together with a limited quantity of tape recorder resources. This made necessary a new concept of real-time image motion compensation.

Miller, Maurine↗
NASA NTRS1991

Lifetime measurement of a collision complex using ion cyclotron double resonance - H2C6N2(+)

In the ion-molecule reaction between HC3N(+) and HC3N, the lifetime of the collision complex (H2C6N2+)-asterisk was long enough that ion cyclotron double-resonance techniques could be used to probe the distribution of the lifetimes of the collision complex. The mean lifetime of the collision complex at room temperature was measured as 180 microsec with a distribution ranging from 60 to 260 microsec as measured at the half-heights in the distribution. Lifetimes of this magnitude with respect to unimolecular dissociation allow for some stabilization of the collision complex by the slower process of infrared photon emission.

Anicich, Vincent G.↗
NASA NTRS1991

Association reactions at low pressure. IV - The HC3N(+)/HC3N system

Ion cyclotron mass spectrometry is used here to study the reactions between HC3N(+) and HC3N and between HC5N(+) and HC3N at pressures from 1 x 10 to the -7th to 0.001 Torr. The former reaction has both a bimolecular reaction path and a termolecular reaction path. The overall bimolecular reaction rate coefficient is 1.3 x 10 to the -19 cu cm/s. The primary product HC5N(+) represents 90 percent of the product ions, while HC6N2(+) and H2C6N2(+) each represent 5 percent. The termolecular association rate coefficient is 3.7 x 10 to the -24th cm exp 6/s, with He as the third body. The mean lifetime of the collision is 180 microsec. HC5N(+) reacts with HC3N to form the adduct ion H2C8N2(+) through both bimolecular and termolecular reactions. The bimolecular rate coefficient is 5.0 x 10 to the -10th cu cm/s and the termolecular one is 1.2 x 10 to the -22nd cm exp 6/s, with HC3N as the third body.

Sen, Atish D.↗
NASA NTRS1990

Principal investigator in a box: Version 1.2 documentation

Principal Investigator (PI) in a box is a computer system designed to help optimize the scientific results of experiments that are performed in space. The system will assist the astronaut experimenters in the collection and analysis of experimental data, recognition and pursuit of 'interesting' results, optimal use of the time allocated to the experiment, and troubleshooting of the experiment apparatus. This document discusses the problems that motivate development of 'PI-in-a-box', and presents a high- level system overview and a detailed description of each of the modules that comprise the current version of the system.

Jurine Adolph↗
NASA NTRS1992

Formaldehyde reactions in dark clouds

The low-pressure reactions of formaldehyde (H2CO) with D(+), D2(+), D3(+), and He(+) are studied by the ion-cyclotron resonance technique. These reactions are potential loss processes for formaldehyde in cores of dark interstellar clouds. The deuterated reactants represent direct analogs for protons. Rate coefficients and branching ratios of product channels have been measured. Charge transfer is observed to be the dominant reaction of H2CO with D(+), D2(+), and He(+) ions. Only the D3(+) reaction exhibits a proton-transfer channel. All reactions proceed at rate coefficients near the collision limit. Proton-deuteron exchange reactions are found to be inefficient processes in the formaldehyde system.

Sen, A. D.↗
NASA NTRS1993

Particulate multi-phase flowfield analysis for advanced solid rocket motor

Particulate multi-phase flowfield with chemical reaction for a 2D advanced solid rocket motor (ASRM) is analyzed using the finite difference Navier-Stokes (FDNS) code. The flowfield in the aft dome cavity of the ASRM is examined and its significant impact on the motor operation and performance is demonstrated. Chemical reaction analysis is performed for H2O, O2, H2, O, H, OH, CO, CO2, Cl, Cl2, HCl, and N2. The turbulent dispersion effect is calculated with the Monte Carlo method. Result show that a recirculation zone exists at the entry of the aft-dome cavity. The particle impingement could cause the erosion and damage nozzle wall. Accumulating in the impingement area the particles change the wall shape and affect the motor performance.

Liaw, Paul↗
NASA NTRS1994

Versatile Dual-Channel Waveform Generator

Programmable waveform generator synthesizes two independent waveforms simultaneously at frequencies up to 250 MHz. Can be in phase or out of phase with each other. Use of commercial integrated circuits helps keep cost low. Operation governed by BASIC source code enabling any user equipped with suitable personal computer to specify waveforms. User can modify source code to satisfy special needs. Other applications include simulation of Doppler waveforms for radar, and of video signals for testing color displays and computer monitors. With eventual substitution of gallium arsenide integrated circuits for its present silicon integrated circuits, instrument able to generate waveforms with 14-bit precision and sample rates as high as 2 GHz.

Staples, Edward J.↗