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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 469 records · Page 26
All sourcesNASA NTRSDOE OSTI
NASA NTRS1971

Evaluation program for secondary spacecraft cells: Acceptance test of McDonnell-Douglas, Astropower division, 40.0 ampere hour silver-zinc cells

The development of an inorganic separator material for use in construction of 40 ampere-hour silver zinc cells is discussed. Acceptance tests were conducted to determine real quality, physical defects and ampere-hour capacity. All acceptance tests were performed at an ambient temperature of 23 to 27 C at existing relative humidity and atmospheric pressure. Of the 63 cells tested, only one failed to meet the equipment specifications.

Harkness, J. D.↗
NASA NTRS1970

Investigation of solid state electrolyte silver-zinc battery

Study of the solid electrolyte ZnCl2-2NH3 rechargeable silver zinc electrochemical cell by X-ray diffraction analysis of the reaction products led to the conclusion that some water is consumed when the cell is discharged. Replacement of ZnCl2-2NH3 by ZnCl2-4Zn(OH)2 gave cells with high internal resistance and limited capacity. The salt formed by exposing a fibrous membrane saturated with ZnCl2 solution to fumes from ammonium carbonate in a dry desiccator comprised ZnCl2-4Zn(OH)2, ZnCl2,3NH4Cl and a third unidentified component. The temperature coefficient of open circuit EMF was nearly zero over the range from -25 C to 50 C. The internal resistance and polarization increased substantially below -25 C. There is some indication that exposure to 50 C for 29 hours causes some deterioration.

Source record↗
NASA NTRS1972

Automatically activated, 300 ampere-hour silver-zinc cell

A prototype silver zinc cell is reported for which the electrolyte is being stored in a separate tank; the cell is being activated when additional power is required by collapsing the neoprene bellows container and thus forcing the electrolyte into cell through a plastic connection. A solar array is proposed as main power source for the flow actuator.

Hennigan, T. J.↗
NASA NTRS1972

Lifetime estimates for sterilizable silver-zinc battery separators

The lifetime of separator membranes currently employed in the electrolyte environment of silver-zinc batteries was estimated at 3 to 5 years. The separator membranes are crosslinked polyethylene film containing grafted poly (potassium acrylate)(PKA), the latter being the hydrophilic agent which promotes electrolyte ion transport. The lifetime was estimated by monitoring the rate of loss of PKA from the separators, caused by chemical attack of the electrolyte, and relating this loss rate to a known relationship between battery performance and PKA concentration in the separators.

Cuddihy, E. F.↗
NASA NTRS1972

Large Silver Halide Single Crystals as Charged Particle Track Detectors

The trajectory of the particle is made visible under a microscope by the accumulation of metallic silver at regions of the lattice damaged by the particle. This decoration of the particle track is accomplished by exposure of the crystal to light. The decoration of normally present lattice imperfections such as dislocations can be suppressed by the addition to the crystal of less than ten parts per million of a suitable polyvalent metal impurity. An account of some preliminary attempts to grow thin single crystals of AgCl is given also, and suggestions for a more refined technique are offered.

Kusmiss, J. H.↗
NASA NTRS1972

A versatile silver oxide-zinc battery for synchronous orbit and planetary missions.

A new kind of silver-zinc cell has been developed and tested under NASA support which can withstand severe heat sterilization requirements. These cells could be used on planetary lander mission which require wet-stand periods of over a year, a modest number of cycles (400 to 500) and may require dry heat sterilization. The weight advantage of these cells over the traditional nickel-cadmium batteries also makes it an attractive alternative for synchronous orbit service where 400 to 500 cycles would be required over a 5 year period.

Schwartz, H. J.↗
NASA NTRS1973

Cross-hatching at Silver Spur.

Diamond-shaped patterns formed by the intersection of two sets of lineaments were reported near the promontory Silver Spur on Hadley Delta, about 20 km south of the Apollo 15 landing site. O'Keefe et al. (1969) hypothesized concerning a possible interrelation between lunar lineaments, gas flow induced by meteorites and turbulent-flow cross-hatching. Possible causes for the occurrence of the lunar lineaments are discussed. It is pointed out that the evidence does not make it possible to select conclusively either geological structure or lighting effects as the sole cause of the lineaments. Gas flows due to meteorite impact vaporization may also be responsible for the observed patterns.

Rehfuss, D. E.↗
NASA NTRS1974

Silver oxide sorbent for carbon dioxide

Material can be regenerated at least 20 times by heating at 250 C. Sorbent is compatible with environment of high humidity; up to 20% by weight of carbon dioxide can be absorbed. Material is prepared from silver carbonate, potassium hydroxide or carbonate, and sodium silicate.

Colombo, G. V.↗
NASA NTRS1974

Evaluation of commercially supplied silver coated Teflon for spacecraft temperature control usage

A series of tests are described which were performed to evaluate the acceptability of a commercially supplied silver backed teflon thermal control coating relative to teflon previously coated at GSFC. Optical measurements made on numerous samples indicate that the commercial material possesses an average solar absorptance of 0.085, an emittance of 0.76 and an average alpha/epsilon equal to 0.112, all of which are equivalent to the GSFC coated teflon. The emittance of the protective inconel backing was found to be 0.037. The coating is shown to have good adhesion at the Ag-teflon interface and exposure to UV irradiation uncovered no coating irregularities. Temperature cycling over the range -135 C to +200 C produced crazing in the evaporated Ag layer as expected but no delamination was observed. The suitability of Mystik no. 7366 and 3M no. 467 adhesives as bonding agents for the metallized polymer is demonstrated. Various problems associated with production reproducibility and selection of a proper bonding process are discussed.

Heaney, J. B.↗
NASA NTRS1973

Development and fabrication of sealed silver-zinc cells, phase 1

A facility was designed, constructed and equipped for the production of prismatic alkaline rechargeable battery cells using inorganic (ceramic) separators. This unique facility is environmentally controlled and contains separate areas for electrode fabrication, separator processing, cell assembly, cell finishing and testing. An initial production run of 125 sealed silver zinc cells, using inorganic separators, was made in the facility in order to provide samples for baseline performance tests. Ten of these cells were given performance characterization and life cycle tests.

Blake, I. C.↗
NASA NTRS1973

Spaceflight performance of silver coated FEP Teflon as a thermal control surface on the IMP-1 spacecraft

A second surface mirror type coating, vapor deposited silver on FEP Teflon, was used as a thermal control surface for one of the experiments aboard the Imp-I spacecraft. This coating was selected to obtain the low operating temperature required for this experiment. Initial flight temperature of this thermal control surface was -70.5 C, very close to the predicted value of -73 C and at a very satisfactory level. Since temperatures within the spacecraft interior are not at this desired low level, the detectors had to be mounted exterior to the spacecraft with a good view of space, preferably in an area shaded from sunlight. When this latter preference proved unobtainable, the detectors were mounted on an aluminum plate located on the exterior of the spacecraft, parallel to the spin axis but rotating about the solar vector. The mounting plate was approximately 6.5 inches by 7.5 inches by 0.125 inches thick. To achieve the desired temperature level with the mounting plate in such a location, the thermal design had to minimize not only the effects of the relatively warm spacecraft environment but also the effects of the incident solar energy.

Hoffman, R. H.↗
NASA NTRS1974

Study of oxygen gas production phenomenon during stand and discharge in silver-zinc batteries

Standard production procedures for manufacturing silver zinc batteries are evaluated and modified to reduce oxygen generation during open circuit stand and discharge. Production predictions of several variable combinations using analysis models are listed for minimum gassing, with emphasis on the concentration of potassium hydroxide in plate formation. A recommendation for work optimizing the variables involved in plate processing is included.

Source record↗
NASA NTRS1973

A versatile silver oxide-zinc battery for synchronous orbit and planetary missions

A new kind of silver-zinc cell has been developed and tested under NASA support which can withstand severe heat sterilization requirements and does not display the traditional life limiting aspect of zinc electrodes - i.e., shape change. These cells could be used on a planetary lander mission which requires wet-stand periods of over a year, a modest number of cycles (400 to 500) and may require dry heat sterilization. The weight advantage of these cells over the traditional nickel-cadmium batteries makes them also an attractive alternative for synchronous orbit service where 400 to 500 cycles would be required over a five-year period.

Schwartz, H. J.↗
NASA NTRS1975

Preliminary flight prototype silver ion monitoring system, addendum

A number of electrode fabrication techniques are investigated, to achieve an electrode meeting shuttle mission requirements for functional life and stability as well as accuracy and precision of measurement. The instability of a silver bromide column when employed in a closed loop calibration scheme is discussed.

Wilson, R. I.↗
NASA NTRS1976

Development of single cell protectors for sealed silver-zinc cells, phase 1

A single cell protector (SCP) assembly capable of protecting a single silver-zinc (Ag Zn) battery cell was designed, fabricated, and tested. The SCP provides cell-level protection against overcharge and overdischarge by a bypass circuit. The bypass circuit consists of a magnetic-latching relay that is controlled by the high and low-voltage limit comparators. Although designed specifically for secondary Ag-Zn cells, the SCP is flexible enough to be adapted to other rechargeable cells. Eighteen SCPs were used in life testing of an 18-cell battery. The cells were sealed Ag-Zn system with inorganic separators. For comparison, another 18-cell battery was subjected to identical life test conditions, but with battery-level protection rather than cell-level. An alternative approach to the SCP design in the form of a microprocessor-based system was conceptually designed. The comparison of SCP and microprocessor approaches is also presented and a preferred approach for Ag-Zn battery protection is discussed.

Imamura, M. S.↗
NASA NTRS1977

Interpretation of the silver L X-ray spectrum

Silver L X-ray energies were calculated using theoretical binding energies from relaxed orbital relativistic Hartree-Fock-Slater calculations. Theoretical X-ray energies are compared with experimental results.

Chen, M. H.↗
NASA NTRS1977

Preliminary investigation of a sealed, remotely activated silver-zinc battery

Methods necessary to provide a remotely activated, silver zinc battery capable of an extended activated stand while in a sealed condition were investigated. These requirements were to be accomplished in a battery package demonstrating an energy density of at least 35 watt hours per pound. Several methods of gas suppression were considered in view of the primary nature of this unit and utilized the electroplated dendritic zinc electrode. Amalgamation of the electrode provided the greatest suppression of gas at the zinc electrode. The approach to extending the activated stand capability of the remotely activated battery was through evaluation of three basic methods of remote, multi-cell activation; 1) the electrolyte manifold, 2) the gas manifold and 3) the individual cell. All three methods of activation can be incorporated into units which will meet the minimum energy density requirement.

Wheat, C. G.↗
NASA NTRS1978

Silver hydrogen batteries

The feasibility of silver hydrogen batteries was investigated. Cell configurations and cell cycling were discussed. Energy density was found to be 65 to 100 watt hours per kilogram. Electrolyte management was considered critical to the cell's performance. Factors of electrolyte management which were particularly important were: (1) the nature of the separator system, and (2) the amount of electrolyte.

Holleck, G.↗