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  • Other Sources  (3,177)
  • ELECTRONICS AND ELECTRICAL ENGINEERING  (1,637)
  • ASTRONAUTICS (GENERAL)  (1,540)
  • 1980-1984  (1,567)
  • 1975-1979  (1,610)
  • 1945-1949
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  • Other Sources  (3,177)
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Years
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  • 1
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    Astronautics (1977)
    In:  CASI
    Details
    Publication Date: 2009-11-17
    Description: Principles of rocket engineering, flight dynamics, and trajectories are discussed in this summary of Soviet rocket development and technology. Topics include rocket engine design, propellants, propulsive efficiency, and capabilities required for orbital launch. The design of the RD 107, 108, 119, and 214 rocket engines and their uses in various satellite launches are described. NASA's Saturn 5 and Atlas Agena launch vehicles are used to illustrate the requirements of multistage rockets.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Soviet Aircraft and Rockets (NASA-TT-F-770); p 198-271
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  • 2
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    Inflight lightning characteristics measurement system (1979)
    In:  CASI
    Details
    Publication Date: 2005-04-28
    Description: A research data-gathering system being developed for inflight measurement of direct and nearby lightning strike characteristics is described. Wideband analog recorders used to record the lightning scenario are supplemented with high-sample-rate digital transient recorders with augmented memory capacity for increased time resolution of specific times of interest. The endless-loop data storage technique employed by the transient recorders circumvents problems associated with oscilloscopic techniques and allows unattended operation. System integrity and immunity from induced effects is accomplished by fiber-optics signal-transmission links, shielded system enclosures, and the use of a dynamotor for power system isolation.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Florida Inst. of Technol. FAA-Florida Inst. of Technol. Workshop on Grounding and Lightning Technol.; p 105-111
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  • 3
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    Metallurgical processing (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-06
    Description: The metallurgical processing experiments on Skylab were chosen to: (1) elucidate the unknown effects of a low gravity environment on certain processes; (2) determine to what extent nongravitational driven flows operate in the processes; and (3) explore the possibilities of containerless solidification. Welding and brazing experiments were conducted to provide an understanding of solidification mechanics in a weightless environment.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Early Space Expt. in Mater. Process.; 37 p
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  • 4
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    Errors in short circuit current measurements due to spectral mismatch between sunlight and solar simulators (1976)
    In:  CASI
    Details
    Publication Date: 2006-08-09
    Description: For abstract, see N77-26620.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Terrest. Photovoltaic Meas., 2; p 161-182
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  • 5
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    Early space experiments in materials processing: Future programs (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-06
    Description: A list of the present state of knowledge in materials processing is presented. The fluid behavior in a low gravity environment is summarized. Materials processing in the Space Transportation System facility is discussed. Prospects for space commercialization are reported.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Early Space Expt. in Mater. Process.; 16 p
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  • 6
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    Post-Skylab activities (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-06
    Description: The Apollo Soyuz Test Program is described. A modification of the Skylab furnace was developed for the ASTP mission that had a maximum temperature of 1200 C, a programmed cool down to give more uniform growth rates, and a He quench system to shorten the time required to reach allowable touch temperature. The Space Processing Applications Rocket (SPAR) program was initiated to provide some continuity in flight experimentation. Liquid mixing, immiscible alloy solidification, composite materials, bubbles and dispersed particles during solidification, and containerless processing techniques were studied in the SPAR program.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Early Space Expt. in Mater. Process.; 45 p
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  • 7
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    Fluid behavior in low g (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-06
    Description: Several experiments and a number of demonstrations were performed during Skylab to elucidate the behavior of fluids in space. The purposes of these experiments were to confirm hypotheses on how systems would behave in a low-g environment, determine to what extent residual accelerations and nongravity-driven convection affected processes, and provide graphic demonstrations of fluid behavior in space for classroom use and to stimulate new ideas for low-g research.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Early Space Expt. in Mater. Process.; 33 p
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  • 8
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    Possible applications of space processing (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-06
    Description: Numerous applications take advantage of low gravity. These range from research, such as study of basic properties of materials or developing a better understanding of various processes and how they might be controlled, to actual production of unique materials, either in very limited quantities for research purposes to serve as paradigms for determining the limiting results of processes in which gravity effects are removed, or in large quantities, to fill certain high technology needs that cannot be met by other means. Examples of these are given in the following topics discussed: (1) crystal growth; (2) metals, alloys and composite materials (metallurgy); (3) glass and ceramics (containerless processing); (4) fluid and chemical processes; and (5) processing of biological materials.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Early Space Expt. in Mater. Process.; 60 p
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  • 9
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    The evolution of apparatus for materials processing on Skylab (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-06
    Description: The following topics are discussed: (1) the inception of space processing; (2) earth-based experimental activities prior to Skylab (drop tower and research aircraft experiments); (3) preliminary experiments in space (Apollo and sounding rocket experiments); and (4) Skylab experimental facilities. Apparatus for contained materials processing; for brazing in space; and containerless processing are presented and discussed. The Skylab materials processing system and miscellaneous design considerations are also discussed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Early Space Expt. in Mater. Process.; 48 p
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  • 10
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    Modeling of the float zone process (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The interaction of heat, mass, and momentum transport in the floating zone method for growing single crystals from the melt is examined. Methods for detailed numerical simulation of the transport phenomena in a floating zone are developed. Results of the calculations are combined with experiments to determine the effects of solidification induced, surface tension driven, and buoyancy driven convection in establishing dopant redistribution in the melt and the roles of heat transfer in crystal and melt and melt/solid interface shape in determining crystal quality. State of the art finite element techniques were developed for calculating the influence of natural convection in the melt on the shape of a melt/crystal interface and dopant segregation in the crystal. These techniques are demonstrated for solidification by the Bridgman technique. Numerical techniques are developed that calculate the shapes of both the melt/solid and melt/gas interfaces simultaneously with the thermal fields in melt and solid. Models for the fluid flows due to the rotation of the feed and crystal rods are completed and the effects of these flows on dopant segregation are studied, especially in the case of zones longer than can be achieved on Earth.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 175-199
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  • 11
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    Calculations of the surface tensions of liquid metals (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The understanding of the surface tension of liquid metals and alloys from as close to first principles as possible is discussed. The two ingredients which are combined in these calculations are: the electron theory of metals, and the classical theory of liquids, as worked out within the framework of statistical mechanics. The results are a new theory of surface tensions and surface density profiles from knowledge purely of the bulk properties of the coexisting liquid and vapor phases. It is found that the method works well for the pure liquid metals on which it was tested; work is extended to mixtures of liquid metals, interfaces between immiscible liquid metals, and to the temperature derivative of the surface tension.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 169-172
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  • 12
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    Ground based silicon zoning program (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The preparation of building flight hardware and carrying out experiments in space was investigated. The ground based investigation phase A/B of the experimental float zoning of silicon is outlined. The overall program goals, leading to recommending experiments to be done in phase C/D are spelled out. Thermophysical properties which must be accurately known to compare thermophysical models to experimental zoning of silicon are listed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Float Zone Workshop; p 111-124
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  • 13
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    Present growth technology of silicon germanium alloys and possible advantages of microgravity growth (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The growth technology of Silicon-germanium (Si-Ge) alloys and the possible advantages of growth in microgravity is reviewed. The Si-Ge alloys have a continuous variation of bandgap energy from the germanium bandgap to the silicon bandgap. The unusual two slope behavior of Eg versus composition is due to the differences in the conduction band structure between Si and Ge. Below 17% (atomic), the germanium band structure dominates; and above it, the bands are "silicon like". It is found that the growth of Si-Ge alloys in microgravity is very attractive. In particular, the float zone method, in which a liquid zone of controlled starting composition, used to grow a large amount of useful alloy crystal. Large temperature gradients and relatively flat growth interfaces are necessary to obtain homogeneous crystal growth.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 151-163
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  • 14
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    Review of literature surface tension data for molten silicon (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: Measurements of the surface tension of molten silicon are reported. For marangoni flow, the important parameter is the variation of surface tension with temperature, not the absolute value of the surface tension. It is not possible to calculate temperature coefficients using surface tension measurements from different experiments because the systematic errors are usually larger than the changes in surface tension because of temperature variations. The lack of good surface tension data for liquid silicon is probably due to its extreme chemical reactivity. A material which resists attack by molten silicon is not found. It is suggested that all of the sessile drip surface tension measurements are probably for silicon which is contaminated by the substrate materials.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 167-168
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  • 15
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    The historical trend in float zone crystal diameters and power requirements for float zoned silicon crystals (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The power needed to zone silicon crystals by radio frequency heating was analyzed. The heat loss mechanisms are examined. Curves are presented for power as a function of crystal diameter for commercial silicon zoning.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 99-106
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  • 16
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    Electric power needs in space (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The power requirements for specific float zone experiments in space are presented. Power figures for the Space Shuttle and projected available power for advanced vehicles are given. The following power related trends are derived: (1) float zone processing of up to 5 cm diameter silicon and 16.0 cm diameter cadmium telluride can be conducted on a Shuttle pallet mission; (2) float zone processing of up to 8.5 cm diameter silicon for 70% total heating efficiency can be conducted on the initial MEC/space platform; (3) projected available host vehicle power for float zone sample heating; (4) induction heating is found to be the most promising heating method; (5) process control and ease of equipment integration into the host vehicle influence heating method selection.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 89-98
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  • 17
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    Power requirements for space crystal growth (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The need for power to grow silicon of a size suitable to make into devices is addressed. The expected results are tied to available power. The projection of the size of float zone crystals as a function of time is discussed. An accompanying graph shows that 4 in. will be the normally used diameter by 1985 and 5 in. by 1990. Material to be tested in device lines in this time frame should be 4 in. or more. The various power losses, 25 kW with a 50% power efficiency, which is much improved over present RF heating efficiencies.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Float Zone Workshop; p 83-88
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  • 18
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    Role of substrate quality on IC performance and yields (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The development of silicon and gallium arsenide crystal growth for the production of large diameter substrates are discussed. Large area substrates of significantly improved compositional purity, dopant distribution and structural perfection on a microscopic as well as macroscopic scale are important requirements. The exploratory use of magnetic fields to suppress convection effects in Czochralski crystal growth is addressed. The growth of large crystals in space appears impractical at present however the efforts to improve substrate quality could benefit from the experiences gained in smaller scale growth experiments conducted in the zero gravity environment of space.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 65-80
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  • 19
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    Industry needs for silicon crystals and standards (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The trend of the device fabrication industry requirement for larger crystals is reviewed. The ranges of properties and uniformities measurement standards needed for resistivity (four-point probe and spreading resistance) and for the chemical composition of oxygen and carbon impurities are presented.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 59-64
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  • 20
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    Air Force future technical requirements for silicon (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: Technical requirements for silicon-based bulk materials are presented, and related work on other materials and on thin layer silicon is summarized. Programs supported by the Wright-Patterson materials laboratory and the capabilities of the materials laboratory in house characterization facility are listed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 55-58
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  • 21
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    Growth of III-V and II-VI alloy crystals in space by vertical zone leveling (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The process of vertical zone melting of CdTe and InP is illustrated, and the growth of Cd sub x Hg sub (1 - x)Te and InP sub y As sub (1-y) is considered.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 46-54
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  • 22
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    Material and processing needs for silicon solar cells in space (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The technical concerns of NASA in the area of space grade solar cells are summarized. Solar power needs are projected through 1987. The degradation of solar cell performance due to the effects of radiation on impurities and crystal defects and the improved performance of float zone silicon are illustrated. The reduction of oxygen and carbon in float zone silicon allows for much faster low temperature annealing of the defects. The effects of improved crystal purity on cell performance are summarized.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 33-41
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  • 23
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    Float zone space processing rationale (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The role of float zone silicon in integrated circuits is surveyed. The problem of oxygen thermal donors and their inhomogeneous distribution is predicted to be a critical issue.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 42-45
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  • 24
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    The need for growing crystals in space (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: Payoffs of crystal growth in space in the areas of understanding growth and melt flow mechanisms, the growth of more uniform crystals with fewer defects, and the growth of crystals difficult or impossible to grow on Earth are summarized. The advantages of various heating methods are summarized. Critical devices requiring the uniformity and lower defect density of crystals grown in space are listed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Float Zone Workshop; p 23-33
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  • 25
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    The nature of melt process changes in microgravity (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The effects on melt impurities of the lack of buoyancy-driven convection in melts and the gas phase are outlined. Probable effects noted are: retardation of convective flow by a thin adsorbed impurity layer because of surface tension gradients (Marangoni flow); changes in the transport of volatile impurities to the melt surface and the consequent reduction of evaporation; and the change in dependence of evaporation rates on pressure due to the absence of convective flow in the gas next to the melt.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Float Zone Workshop; p 16-19
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  • 26
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    Review of past flight experiments pertinent to float zone (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: Materials processing experiments performed in space since 1973 are listed. Experiments carried out in Skylab, the Apollo Soyuz mission, and on SPAR sounding rockets are included.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Float Zone Workshop; p 13-15
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  • 27
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    Float Zone Workshop, introduction (1981)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The purposes of the float zone working group are summarized. Present and proposed U.S. and European research programs are listed, and power needs for float zoning surveyed. A 1981 to 1991 schedule for development efforts is presented.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Float Zone Workshop; p 1-10
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  • 28
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    NASA workshop on outgassing (1979)
    In:  CASI
    Details
    Publication Date: 2006-06-20
    Description: The materials and processing constraints that are involved in the construction of a molecular wake shield for the shuttle orbiter are discussed. Stainless steel, having outgassing rates less than the required 10 to the minus 12th power Torr-liters/sq cm per second was the primary material suggested for the construction of the shield.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Proc. of Workshops to Define Eng. Requirements for a Space Vacuum Res. Facility; 17 p
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  • 29
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    Report of the Ad Hoc Committee on the assessment of models of a wake shield environment around various spacecraft, Universities Space Research Association (1979)
    In:  CASI
    Details
    Publication Date: 2006-06-20
    Description: Models depicting the ambient atmosphere which can overtake the spacecraft vacuum shield are presented. The subject areas discussed are: possible changing effects on the wake shield environment; possible utilization of the induced environmental contamination monitor; present state of the knowledge of the parameters used to describe the intermolecular collisions; the possibility of using simple models to describe the wake shield environment; possible errors associated with using kinetic theory to calculate that part of the atmosphere overtaking the shield; and a general assessment of the Monte Carlo techniques used to calculate the shield environment.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Proc. of Workshops to Define Eng. Requirements for a Space Vacuum Res. Facility; 6 p
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  • 30
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    Proceedings of workshops to define engineering requirements for a space vacuum research Facility: Summary (1979)
    In:  CASI
    Details
    Publication Date: 2006-06-20
    Description: Models depicting the collision dynamics in the near vicinity of a body orbiting in the upper atmosphere were studied to investigate degassing techniques for a vacuum facility.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Proc. of Workshops to Define Eng. Requirements for a Space Vacuum Res. Facility; 3 p
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  • 31
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    Space environment effects (M0006) (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The effects of long term exposure to the near Earth space environment on advanced electrooptical and radiation sensor components were examined. The effect of long duration spaceflight on the germination rate of selected terrestrial plant seeds is observed in exobiological experiments.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Langley Research Center Long Duration Exposure Facility (LDEF); p 185-187
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  • 32
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    Test methods and results of the 10-cell bipolar Ni-H2 battery (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Characterization tests were carried out at three charge levels and four discharge levels. The "c' or capacity of the battery is designated at 6.5 ampere-hours. The recharge ampere-hours was the same for all test conditions, 6.5 A-H, regardless of the discharge capacity removed for any particular discharge rate. Less capacity can be removed at higher discharge rates to the same termination voltage, which was 0.50 volts for the weakest (lowest voltage) cell. The general trend of efficiencies increases as the charge rate increases as noted in results of the table included in the handout package. The data also indicate the efficiency increases as the discharge rate decreases. This is true; however, efficiencies at the discharge rates of c and 2c are penalized because these cycles received more overcharge than necessary.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 496-500
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  • 33
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    Determination of the reliability of Ni-Cd batteries from survival data on cells fabricated 1964 - 1977 (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The probability of Ni-Cd battery survival was determined by researching survival data on cells fabricated from 1964-1977. A log of cell failure times were plotted against cumulative failure percentage and mean and standard deviation were determined.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 470-479
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  • 34
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    Experimental design (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The design of long life, low weight nickel cadmium cells is studied. The status of a program to optimize nickel electrodes for the best performance is discussed. The pore size of the plaque, the mechanical strength and active material loading are considered in depth.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 253-469
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  • 35
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    Advanced nickel hydrogen cell configuration study (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: An evaluation of the current nickel hydrogen cell design is presented. The IPV, or the Individual Pressure Vessel, is the state of the art right now. The present design, 3 1/2 inch cell, has a current limit of 50 ampere-hours. The nickel hydrogen cell design is the state of the art. Its size is 3 1/2 inches which limits it to 50 hours. The probable limits of that are probably 160 amphere IPV cell remaining in the passive cooling mode. The IPV stacks is a parallel connection of electrodes. Positive electrodes are connected with leads to the top portion of the stack and negative electrodes are connected with leads and pulled down to the bottom. So it is a combination connection of paralleling series electrostacking--parallel inside each individual stack, and series connected from one stack to the next. It offers, in the analysis, improvements in packaging, cost, energy density, and specific energy.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 480-495
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  • 36
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    Nickel hydrogen/nickel cadmium battery trade studies (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Nickel Hydrogen cell and battery technology has matured to the point where a real choice exists between Nickel Hydrogen and Nickel Cadmium batteries for each new spacecraft application. During the past few years, a number of spacecraft programs have been evaluated at Hughes with respect to this choice, with the results being split about fifty-fifty. The following paragraphs contain criteria which were used in making the battery selection.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 430-438
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    Canadian experience with nickel cadmium systems (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The Defense Research Establishment Ottawa (DREO) has been studying the nickel-cadmium system, both vented and sealed, since the early 1950's. Reasonable success has been achieved in a wide variety of applications covering: military vehicle use under Arctic conditions; high performance military aircraft; manpacked communications sets; remote standby power and small portable instrumentation. Early studies on the vented system for high rate vehicle and aircraft cranking applications proved useful in later studies on the sealed NiCd system. This was especially true in the areas of plate loading and electrolyte composition. To achieve high rate cranking currents of 20C to 30C, it was necessary to have light to moderate plate loadings, a large reactive surface area, and electrolyte of optimum conductivity. DREO undertook some fundamental studies to understand the system from the inside out rather than test cells from the outside and then analyze their components. The conclusions of these studies were incorporated into the Procurement Specification for Ni-Cd cells ISISA Spec S615-P-2. A brief comment will be made on the choice of cell design and how some of the factors of cell manufacture could affect cell performance.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 439-451
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  • 38
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    Real and potential nickel hydrogen superiority (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Events from the development and orbital flight experience with a nickel hydrogen battery are described. The events highlight characteristics of nickel hydrogen which afford superior capability in overcharge, overdischarge and state of charge evaluation, when compared to the nickel cadmium electrochemical system. Some developments in nickel hydrogen technology that provide the potential of furthering nickel hydrogen superiority for satellite applications are also discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 416-429
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  • 39
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    Ni-H2 batteries for communications satellites (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Ni-H2 batteries are just now being put into service. All of the remaining INTELSAT V satellites (approximately 10), starting with the next to be launched in early 1983, will use Ni-H2 batteries. In addition, the next generation of INTELSAT VI satellites, and probably INTELSAT VII and VIII, will use Ni-H2 batteries. This means that international telecommunications satellites will use Ni-H2 batteries through the 1990's. It is projected that the lifetime of these batteries will be greater than 10 years at deep depth-of-discharge (DOD), and that the battery subsystem will no longer limit satellite lifetime or communications capability during eclipse periods. This paper discusses the advantages of the Ni-H2 battery, as compared with the Ni-Cd battery, for telecommunications satellites.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 389-415
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  • 40
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    Status of SAFT silver hydrogen cell development (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Nickel-hydrogen cells appear to be an improvement over the nickel-cadmium in applications requiring longer lifetime and reduced weight. An even more efficient couple, the silver-hydrogen couple, is also considered. After a theoretical study first performed by the Battelle Institute of Geneva under ESA (European Space Agency) contract, SAFT has undertaken more detailed analyses of the silver-hydrogen degradation mechanisms. ESA and the French Department of Defense contracted with SAFT for a full-development program of the silver-hydrogen technology.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 347-371
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  • 41
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    Reconditioning and the nickel electrode (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: This effects of reconditioning on the performance of NiCd batteries are reviewed. These effects are correlated with cell experiments and individual electrode investigations. The effects of reconditioning on the positive electrode performance are found to be significant. A mechanism is proposed that rationalizes the operation of the nickel electrode and suggests that reconditioning minimizes depth of discharge stress during use and maintains uniformity of the active material.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 324-345
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  • 42
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    Spacecraft battery reconditioning cost considerations (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Cost considerations for spacecraft battery reconditioning are studied. Results indicate that the cost of performing reconditioning is minuscule compared with spacecraft system investment. Results also indicate that spacecraft life extension of a few days justifies incorporation of reconditioning circuitry.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 303-310
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  • 43
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    Unique battery reconditioning cycle for RCA's geostationary satellites and its applicability for low Earth satellite (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Six (6) geostationary spacecraft, manufactured by RCA Astro, are presently operating in orbit. All of their batteries are performing well. They all contain unique battery reconditioning circuitry, permitting individual cell reconditioning to practically zero volts without the danger of cell reversal. This reconditioning is performed just prior to start of each eclipse season. This technique has maintained the battery's end-of-discharge voltage with mission life. The oldest operating RCA Astro geostationary spacecraft, Satcom F1 and F2, have now completed almost 7 and 6-3/4 years in orbit, respectively. Their battery performance, reported herein, show that a major milestone in the mission longevity of nickel-cadmium batteries has heen achieved. Low earth orbit test data show a long lasting effect of maintaining end-of-discharge voltages for nickel cadmium cells using periodic reconditioning. The unique RCA light-weight reconditioning circuitry can accomplish a quick reconditioning and prevent cell reversal. Reconditioning, thus, has the potential for extending mission life of geostationary as well as low earth orbit spacecraft, when two or more batteries are present.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 311-323
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  • 44
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    Deep discharge reconditioning: Pros and cons (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Deep-discharge reconditioning (DDR) can be of great benefit to battery performance, especially in geosynchronous orbit, if performed properly and regularly, and can be essential to operation of batteries at the high depths of discharge (DOD) required to minimize weight. The procedure should be tailored to fit the nature of the degradation occuring during regular cycling. DDR is not without its drawbacks, however, and these differ depending on the normal DOD to be sustained and/or whether the discharge is done at the battery or the cell level. Battery-level discharge carries the minimum weight penalty but raises questions of the effects of low-rate cell reversal that as yet have no firm answers. Cell level discharge avoids cell reversal but carries significant penalties of weight and complexity. Thus no universal procedure or method of implementation of deep-discharge reconditioning is now available and thus the various approaches must be evaluated for each application.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 297-302
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  • 45
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    Control requirements for future battery systems (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: It is argued that sophisticated battery control systems are required to support the high power, high energy spacecraft secondary battery systems of the post 1985 time period. Four categories of battery control system functions are defined and discussed: battery operational control, auxiliary system control, battery system status indication and fault detection fault isolation. A concept for implementation of such a control system is also presented and discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 270-279
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  • 46
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    A comparison of voltage limit charge control for fixed array and sun oriented array missions (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A comparison of voltage limited control methods limit control methods for fixed array and oriented array missions is given. The LANDSAT D, Earth Radiation Budget Experiment and Solar maximum Mission techniques are compared.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The 1982 Goddard Space Flight Center Battery Workshop; p 231-258
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  • 47
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    Battery charge control with temperature compensated voltage limit (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Battery charge control for orbiting spacecraft with mission durations from three to ten years, is a critical design feature that is discussed. Starting in 1974, the General Electric Space Systems Division designed, manufactured and tested battery systems for six different space programs. Three of these are geosynchronous missions, two are medium altitude missions and one is a near-earth mission. All six power subsystems contain nickel cadmium batteries which are charged using a temperature compensated voltage limit. This charging method was found to be successful in extending the life of nickel cadmium batteries in all three types of earth orbits. Test data and flight data are presented for each type of orbit.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 259-269
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  • 48
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    Computer modeling of batteries from non-linear circuit elements (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A simple non-linear circuit model for battery behavior is given. It is based on time-dependent features of the well-known PIN change storage diode, whose behavior is described by equations similar to those associated with electrochemical cells. The circuit simulation computer program ADVICE was used to predict non-linear response from a topological description of the battery analog built from advice components. By a reasonable choice of one set of parameters, the circuit accurately simulates a wide spectrum of measured non-linear battery responses to within a few millivolts.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 201-215
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  • 49
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    Modeling a Li/SOCl2 battery for design purposes (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A generalized code applicable to many different electrochemical systems and geometric designs is discussed. The code is to be set up so that physical property data such as thermal conductivity, viscosity, density, and configuration (e.g. physical dimensions) are the input data. Thus, by changing these parameters many different battery configurations can be handled. The outputs, as a function of time and space, are voltage, current, temperature, pressure, velocity, and species concentration.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 178-199
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  • 50
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    Fitting voltage curves with an electrochemically derived equation (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Previous work is refined and extended to describe the discharge curve of Ni-Cd cells. Several models are discussed which are based on chronopotentiometry theory and on a thermodynamic approach. Emphasis is placed on improvement of the fit for the initial portion of discharge. Equations are presented which improve the fit for all regions of the discharge curve.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 164-177
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  • 51
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    Battery model for electrical power system energy balance (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A model to simulate nickel-cadmium battery performance and response in a spacecraft electrical power system energy balance calculation was developed. The voltage of the battery is given as a function of temperature, operating depth-of-charge (DOD), and battery state-of-charge. Also accounted for is charge inefficiency. A battery is modeled by analysis of the results of a multiparameter battery cycling test at various temperatures and DOD's.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 117-124
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  • 52
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    Validating cell/battery safety (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Using the accelerating rate calorimeter, the hazards associated with exothermic reactions occurring in Li/SO2 cells under the conditions of discharge, forced overdischarge, resistive overdischarge, and forced overdischarge at low tempratures are quantitatively defined in terms of: rate of pressure generation, overall pressure rise, rate of temperature, and overall heat generation. Consistent with the findings of other investigators, it is believed that the major reactions contributing to Li/SO2 cell exothermicity are: the lithium/acetonitrile reaction, the thermal decomposition of lithium dithionite, and the lithium/sulfur reaction.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 85-99
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  • 53
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    Design of a safe cylindrical lithium/thionyl chloride cell (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Cell design criteria were established which can result in a safe lithium/thionyl chloride cell. A cell vent, a low area internal anode cell, cell balance and composition of the cathode-electrolyte solution were found to be important factors in the design of a safe cell. In addition to routine testing, both undischarged and discharged cells were subjected to electrical abuse, environmental abuse and mechanical abuse without disassembly.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 75-84
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  • 54
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    Controlling hazardous reactions during voltage reversal of high energy lithium cells (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The roll of general cell design characteristics in preventing hazardous reactions during voltage reversal of lithium cells is discussed. Anode limited versus cathode limited design and case positive versus case negative design are addressed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 67-74
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  • 55
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    Safety tests (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The ovedischarge test program and results for double A and D lithium cells are discussed. Temperature increases and sparking responses are dressed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 60-63
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  • 56
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    Low temperature performance tests (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Lithium cell performance at extremely low temperatures was tested and materials which could be used to make a cell completely electro-chemically inert for the purpose of deactivation were investigated. The effects of temperature and current density on polarization and performance loss are discussed along with discharge recovery behavior.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 64-66
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  • 57
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    Policies governing the use of lithium batteries in the Navy (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Lithium batteries offer many advantages for Navy systems but may also exhibit undesirable hazardous behavior. Safety problems have been traced to a variety of chemical and physical causes. The Navy has established a central safety office with responsibility for all lithium battery use. Before an item is approved for Navy use, it must pass both a design review and a set of end item tests. These reviews focus on complete systems which include a battery inside the end item. After system approval, specific regulations govern the transportation, storage, and disposal of the unit containing lithium batteries. Each of these areas is discussed in detail.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 23-34
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  • 58
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    The Galileo probe Li/SO2 battery: The safest battery on Jupiter (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The unique power requirement of NASA's Galileo Jupiter Probe are most readily met by a Li/SO2 battery; however, because this battery system is not space flight proven, extensive effort was required to qualify this device from the stand point of performance and safety. Due to the rather checkered safety record of the Li/SO2 system, safety has been foremost among the design considerations and has been addressed at the cell, battery and system level. The mission requirements which led to the choice of the Li/SO2 battery and the safety engineering which went into the battery and power system design are described.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 15-22
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  • 59
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    forced overdischarge related safety aspects of Li/SO2 and Li/SOCl2 cells (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Results of an experiment investigating overdischarge behavior of two types of Li/SO2 cells are presented. Forced overdischarges of the Li/LiBr, CH3CN/SO2 cell can result in unsafe behavior such as venting with fire and release of toxic gases. The hazards may be minimized or eliminated by careful cell design considerations and practice of high standards of quality contol in cell manufacture. Seemingly safe cells at 25 C when forced overdischarged at -25 C, even at low currents, exhibited incipient signs of hazards. Their cathodes indicated signs of shock sensitivity. Cathode limited Li/SOCl2 cells were safe during forced overdischarge for long periods of time. Lithium limited Li/SOCl2 cells in which practically all Li had been used up before cell reversal did not exhibit hazardous behavior. Anode limited Li/SOCl2 cells, but not Li limited, exhibited detonations, all during overdischarges at relatively low current densities of or = 1 mA/sq cm 2. Anode potentials 4v with large oscillations preceeded the events. The events were confined to the anode and the temperature rose high enough to melt Ni grids.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 47-59
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    Primary lithium batteries, some consumer considerations (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: In order to determine whether larger size lithium batteries would be commercially marketable, the performance of several D size lithium batteries was compared with that of an equivalent alkaline manganese battery, and the relative costs of the different systems were compared. It is concluded that opportunities exist in the consumer market for the larger sizes of the low rate and moderate rate lithium batteries, and that the high rate lithium batteries need further improvements before they can be recommended for consumer applications.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 35-45
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    Hazardous behavior of lithium batteries. Case histories (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Case histories were described of hazardous behavior for three different cell sizes ranging in nominal capacity from 300 mAh to 12,000 Ah. Design characteristics and other facts believed to have been responsible for the cell explosions, are presented. Obvious facts are discussed as causes for hazardous behavior of lithium batteries in general and oxyhalide batteries in particular.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 3-14
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  • 62
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    Electrophoresis of biological materials (1975)
    In:  CASI
    Details
    Publication Date: 2006-04-10
    Description: The selection of biological products was studied for electrophoresis in space. Free flow electrophoresis, isoelectric focusing, and isotachophoresis are described. The candidates discussed include: immunoglobulins and gamma globulins; isolated islet of langerhans from pancreas; bone marrow; tumor cells; kidney cells, cryoprecipitate; and column separated cultures.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Econ. Analysis of Materials Processing in Space; p 177-190
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    High purity tungsten targets (1975)
    In:  CASI
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    Publication Date: 2006-04-10
    Description: High purity tungsten, which is used for targets in X-ray tubes was considered for space processing. The demand for X-ray tubes was calculated using the growth rates for dental and medical X-ray machines. It is concluded that the cost benefits are uncertain.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Econ. Analysis of Materials Processing in Space; p 159-176
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  • 64
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    Costs and benefits of turbine blades (1975)
    In:  CASI
    Details
    Publication Date: 2006-04-10
    Description: The potential demand for space processed turbine blades, and the dollar benefits to be derived from this technology were analyzed. It was found that an adequate demand to justify space processed blades will exist. The cost benefits per blade for replacements in existing aircraft is estimated to be $997.50 per blade, and for new aircraft the savings per blade would be over $21,000.00.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Econ. Analysis of Materials Processing in Space; p 40-90
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    Materials science (1981)
    In:  CASI
    Details
    Publication Date: 2006-06-04
    Description: The first Spacelab space processing payload includes the following categories of hardware: (1) multiuser facilities, (2) common-support equipment, and (3) six autonomous experiments. All the hardware, with the exception of two elements (covering three experiments), will be integrated in a Spacelab double rack called the materials science double rack. The payload experimental facilities are intended to perform, during the first Spacelab mission, a number of significant pilot experiments in the fields of crystal growth, fluid physics and metallurgy, and, at the same time, to flight-verify the materials science hardware items developed (e.g., various furnaces, process chambers, etc.).
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Spacelab Mission 1 Expt. Descriptions; 16 p
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  • 66
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    Waveguide arc study (1979)
    In:  CASI
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    Publication Date: 2006-06-01
    Description: Research on waveguide arcs is presented as well as an evaluation on an arc detector. Ways of improving the radio frequency arc generation include methods of generating RF arcs inside the resonator. Dc nitrogen arcs were used to study a spectroradiometer. The spectral strucutres obtained provide a general sketch of spectral distribution and their relative magnitude. The upgrading of a transmitter test light and the simulation of an LED array are reported.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Deep Space Network; p 196-203
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  • 67
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    A transmission line phase stabilizer (1979)
    In:  CASI
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    Publication Date: 2006-06-01
    Description: To meet the phase stability requirements of certain experiments performed with the Deep Space Network, transmission lines carrying reference signals must be stabilized to reduce changes in their electrical length due to mechanical movement or changes in ambient temperature. A transmission line phase stabilizer being developed at JPL to perform this function is described.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Deep Space Network; p 67-71
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    The ac power line protection for an IEEE 587 Class B environment (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The 587B series of protectors are unique, low clamping voltage transient suppressors to protect ac-powered equipment from the 6000V peak open-circuit voltage and 3000A short circuit current as defined in IEEE standard 587 for Category B transients. The devices, which incorporate multiple-stage solid-state protector components, were specifically designed to operate under multiple exposures to maximum threat levels in this severe environment. The output voltage peaks are limited to 350V under maximum threat conditions for a 120V ac power line, thus providing adequate protection to vulnerable electronic equipment. The principle of operation and test performance data is discussed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Langley Research Center Intern. Aerospace and Ground Conf. on Lightning and Static Elec.; 5 p
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    Drop dynamics (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The drop dynamics module is a Spacelab-compatible acoustic positioning and control system for conducting drop dynamics experiments in space. It consists basically of a chamber, a drop injector system, an acoustic positioning system, and a data collection system. The principal means of collecting data is by a cinegraphic camera. The drop is positioned in the center of the chamber by forces created by standing acoustic waves generated in the nearly cubical chamber (about 12 cm on a side). The drop can be spun or oscillated up to fission by varying the phse and amplitude of the acoustic waves. The system is designed to perform its experiments unattended, except for start-up and shutdown events and other unique events that require the attention of the Spacelab payload specialist.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Spacecraft Dyn. as Related to Lab. Expt. in Space; p 32-33
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    Detection and analysis of radio frequency lightning emissions (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The feasibility study of detection of lightning discharges from a geosynchronous satellite requires adequate ground-based information regarding emission characteristics. In this investigation, a measurement system for collection of S-band emission data is set up and calibrated, and the operations procedures for rapid data collection during a storm activity developed. The system collects emission data in two modes; a digitized, high-resolution, short duration record stored in solid-state memory, and a continuous long-duration record on magnetic tape. Representative lightning flash data are shown. Preliminary results indicate appreciable RF emissions at 2 gHz from both the leader and return strokes portions of the cloud-to-ground discharge with strong peaks associated with the return strokes.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 20 p
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    A BAPTA employing rotary transformers, stepper motors and ceramic ball bearings (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The utilization of rotary transformers as an alternative to slip rings for the power transfer from solar panels to a satellite's main body could be advantageous, especially if an ac bus system is taken into consideration. Different approaches with main emphasis on the electromagnetic design were investigated and showed efficiencies of up to 99% with a 3 kW power capability. A solidly preloaded pair of ball bearings with ceramic balls assures proper transformer air gaps and acceptable torque changes over temperature and temperature gradients. The bearing and power transfer assembly is driven by a direct drive stepper motor with inherent redundancy properties and needs no caging mechanism.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 189-203
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    Coalignment of spacecraft experiments (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: On February 14, 1980, the solar maximum mission (SMM) satellite was launched into orbit with experiments to monitor solar activity. In order to obtain common object observations, experiments must be coaligned within 90 arc-seconds of the spacecraft pointing vector. Hardware designed to minimize structural and thermal distortions of the experiment support plate is described. Coalignment was provided through control of interface which combined flexible blades to limit load transfer and spherical seats for alignment reference.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 91-113
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    The design and evaluation of superconducting connectors (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The development of a superconducting connector for superconducting circuits on space flights is described. It is proposed that such connectors be used between the superconducting readout loop and the SQUID magnetometer in the Gravity Probe B experiment. Two types of connectors were developed. One type employs gold plated niobium wires making pressure connections to gold plated niobium pads. Lead-plated beryllium-copper spring contacts can replace the niobium wires. The other type is a rigid solder or weld connection between the niobium wires and the niobium pads. A description of the methods used to produce these connectors is given and their performance analyzed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 10 p
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  • 74
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    Skylab: A beginning (1977)
    In:  CASI
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    Publication Date: 2006-01-16
    Description: A major goal of Skylab was to learn more about man and his responses to the space environment for missions lasting up to 84 days. A review of Skylab data pertaining to this goal is given.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Biomed. Results from Skylab; p 408-418
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  • 75
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    A survey of Rocketry and astronautics in Spain (1977)
    In:  CASI
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    Publication Date: 2006-01-16
    Description: The entire field of rocketry and astronautics in Spain was studied. Congreve war rockets in military actions were emphasized in the African war, the Cuban campaign and the Spanish Civil War. Rockets in space travel were also summarized along with space science fiction.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 78-101
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    On the works of S. S. Nezhdanovsky in the field of flight based on reactive principles, 1880 - 1895 (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The work of a Soviet scientist and inventor of the 19th century, S. S. Nezhdanovsky, is discussed. Investigations in the field of aircraft science and technology are emphasized in relation to Nezhdanovsky's studies of using the jet principle in solving the problem of human flight. Nezhdanovsky dealt with calculations of the speed at which combustion products flow, and considered such problems as fuel feeding into the combustion chamber by means of pumps, and the use of one of the fuel components for cooling the walls of the combustion chamber.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 125-139
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  • 77
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    History of the development of rocket technology and astronautics in Poland (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The development of rocket technology in Poland is outlined. The history cites 13th century use of war rockets in combating Tartars as well as 20th century studies of the future and reality of space flights.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 102-111
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  • 78
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    First works by K. E. Tsiolkovsky and I. V. Meshchersky on rocket dynamics (1977)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: A study of rocket dynamics done by K. E. Tsiolkovsky in 1896 is reported. Problems in rectilinear movement of rockets were studied. Calculations were done on velocity efficiency, motion in free space, motion in a homogeneous gravitational field and motion with constant acceleration.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 115-124
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  • 79
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    Platforms in space: Evolutionary trends (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The problem of physical crowding and the proliferation of separate communication links and ground support systems for multiple free-flying satellites can be overcome by using space platforms and multiplexing the data streams. Pertinent features of the space shuttle orbiter payloads, the solar power satellite, and geostationary and geosynchronous platforms are discussed. Typical payload requirements data which are needed to allow meaningful study of payloads as candidates for platform implementation are cited and factors affecting the compatibility/grouping of payloads are outlined.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Proc.: Workshop on the Need for Lightning Observations from Space; p 159-182
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  • 80
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    Guido von Pirquet: Austrian pioneer of astronautics (1977)
    In:  CASI
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    Publication Date: 2006-01-16
    Description: The works of Guido von Pirquet, Austrian pioneer of rocketry, were assessed. Major emphasis was given to Pirquet's calculation of the route to Venus which in fact was followed by the first Russian rocket to Venus. Of interest also is Pirquet's valuable construction of a space station and his analysis of interstellar space flight.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA, Washington Essays on the History of Rocketry and Astronautics, Vol. 1; p 140-155
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  • 81
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    Progress Report on Project Mercury (1976)
    In:  CASI
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    Publication Date: 2006-01-16
    Description: Progress on Project Mercury, program for manned orbital space flight, is briefly reviewed. The original aims and concepts of the project are recounted. Various types of launch apparatus are mentioned along with safety factors.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Collected Works of Charles J. Donlan; 6 p
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  • 82
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    Guidelines for advanced manned space vehicle program, June 1960 (1976)
    In:  CASI
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    Publication Date: 2006-01-16
    Description: A very broad mission objective was established; i.e., manned circumlunar flight and return to earth. It is implicit that the Saturn will be the primary propulsion system for this mission. The following attempts to: (1) define the objective so as to achieve as much capability in the vehicle as possible; (2) draw on Mercury experience to provide broad guidelines for vehicle performance and safety; (3) provide flexibility in the vehicle capability in the event that the manned lunar mission is proved to be subject to unacceptable risk in the target time period; and (4) indicate problem areas where work appears to be particularly needed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Collected Works of Charles J. Donlan; 66 p
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  • 83
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    Extraction processes for the production of aluminum, titanium, iron, magnesium, and oxygen and nonterrestrial sources (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The suitability of existing terrestrial extractive metallurgical processes for the production of Al, Ti, Fe, Mg, and O2 from nonterrestrial resources is examined from both thermodynamic and kinetic points of view. Carbochlorination of lunar anorthite concentrate in conjunction with Alcoa electrolysis process for Al; carbochlorination of lunar ilmenite concentrate followed by Ca reduction of TiO2; and subsequent reduction of Fe2O3 by H2 for Ti and Fe, respectively, are suggested. Silicothermic reduction of olivine concentrate was found to be attractive for the extraction of Mg becaue of the technological knowhow of the process. Aluminothermic reduction of olivine is the other possible alternative for the production of magnesium. The large quantities of carbon monoxide generated in the metal extraction processes can be used to recover carbon and oxygen by a combination of the following methods: (1) simple disproportionation of CO,(2) methanation of CO and electrolysis of H2O, and (3) solid-state electrolysis of gas mixtures containing CO, CO2, and H2O. The research needed for the adoption of earth-based extraction processes for lunar and asteroidal minerals is outlined.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Ames Res. Center Space Resources and Space Settlements; p 257-274
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  • 84
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    The initial lunar supply base (1979)
    In:  CASI
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    Publication Date: 2006-01-12
    Description: The first lunar supply base should have a mass less than 1000 tons, be deployed by 24 persons in 4 months, and be maintained by 10 persons. Output could be expanded 20 times in 5 years to 600,000 tons/yr by a factor of 10 expansion of the area of the solar array on the lunar surface, using low power soil beneficiation, increasing the fleet of mining vehicles, and illuminating the base continuously at night with lunar orbiting mirrors. The space manufacturing facility (SMF) will supply most of the mass (solar cells and orbiting mirrors) necessary for expansion. Several devices and procedures are suggested for development which could further reduce the total mass necessary to transport to the Moon to establish the initial lunar supply base.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Ames Res. Center. Space Resources and Space Settlements; p 207-224
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  • 85
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    Zero-G processing of magnets experiment MA-070 (1976)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Solidification of magnetic materials in the low gravity orbital environment was studied. The magnetic compounds under study, manganese bismuth and copper cobalt cerium ((Cu, Co)5Ce), both have the potential for the development of high coercive strength. Preliminary results indicate that static fluid configurations, in the absence of the gravitational body force, differ substantially from the documented terrestrial behavior. Chemical homogeneity is substantially enhanced on a macroscopic and microscopic level. Single crystal matrices have been grown in the coordinated growth regions of the flight samples. Primary crystals one order of magnitude greater than those grown terrestrially have been noted and are limited in size by the ampoule dimensions.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Lyndon B. Johnson Space Center Apollo-Soyuz Test Project; 13 p
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  • 86
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    A 100-kHz frequency divider, distribution amplifier (1975)
    In:  CASI
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    Publication Date: 2006-01-12
    Description: A frequency divider, distribution amplifier module having low phase noise and low phase drift with temperature and high isolation between outputs was developed for use in the hydrogen maser frequency standard, where it divides 1 MHz from the previous frequency divider down to 100 kHz and provides four transistor-transistor logic (TTL) outputs.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Deep Space Network; p 102-104
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  • 87
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    Induced electric currents in the Alaska oil pipeline measured by gradient, fluxgate, and SQUID magnetometers (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The field gradient method for observing the electric currents in the Alaska pipeline provided consistent values for both the fluxgate and SQUID method of observation. These currents were linearly related to the regularly measured electric and magnetic field changes. Determinations of pipeline current were consistent with values obtained by a direct connection, current shunt technique at a pipeline site about 9.6 km away. The gradient method has the distinct advantage of portability and buried- pipe capability. Field gradients due to the pipe magnetization, geological features, or ionospheric source currents do not seem to contribute a measurable error to such pipe current determination. The SQUID gradiometer is inherently sensitive enough to detect very small currents in a linear conductor at 10 meters, or conversely, to detect small currents of one amphere or more at relatively great distances. It is fairly straightforward to achieve imbalance less than one part in ten thousand, and with extreme care, one part in one million or better.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Solar-Terrest. Predictions Proc., Vol. 2; p 182-192
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  • 88
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    Prediction of solar induced currents and effects on power transmission systems in central Canada (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The auroral-electrojet zone covers three quarters of Manitoba and consequently, solar storms strongly affect transmission lines. Harmonics are generated at transformers due to the saturation of their cores by induced currents, and the level of harmonics produced may cause malfunction of control relays, and yield unacceptable distortions in normal ac waveforms. The expected effects of long ac transmission systems were studied with emphasis on a 500 kv line to be built from Winnipeg to Minneapolis-St. Paul. Spectral analysis of induced current records from Manitoba Hydro's LaVerendrye station and magnetograms from IMS stations in Manitoba were used along with results of Campbell's work on the Alaskan pipeline induction problem (1978) in order to predict periodic and surge currents. It is concluded that the surge currents will produce significant levels of harmonics and corresponding operating problems during magnetic storms.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Solar-Terrest. Predictions Proc., Vol. 2; p 162-171
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  • 89
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    Harmonics of 60 Hz in power systems caused by geomagnetic disturbances (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Simultaneous VLF/ULF observations carried out near Winnipeg, Manitoba show that geomagnetic disturbances control the behavior of harmonics of 60 Hz man-made electric power. The harmonics of 60 Hz detected by the VLF receiver are at multiples of 180 Hz, indicating that they originated from a 3 phase ac power system. Under geomagnetically quiet conditions, only odd harmonics of 70 Hz were detected. In disturbed conditions, both odd and even harmonics were excited. The strength of each harmonic changed concurrently with geomagnetic pulsation (ULF) activity. These findings seem to indicate that a portion of telluric currents shunted into the power line system through the neutrals of the Y-connected transformers give rise to a dc bias to the transformer core materials and that it distorts their hysteresis loops, activating harmonics of 60 Hz power. A mathematical proof is given that a hysteresis loop having a point of symmetry generates odd harmonics only, whereas loops lacking in point-symmetry generally give rise to both odd and even harmonics. A general formula was obtained to calculate the strength of each harmonic based on the shape of the hysteresis loop.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Solar-Terrest. Predictions Proc., Vol. 2; p 172-181
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  • 90
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    The problem of solar induced currents (1979)
    In:  CASI
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    Publication Date: 2006-01-16
    Description: The production of surface electric fields by geomagnetic variations is discussed with reference to magnetotelluric theory; and evidence is presented to show that the severity of solar-induced currents (SIC) at Cornerbrook, Newfoundland is due to channeling of currents induced in the sea through a region adjacent to the power line. An 'isolated loop' approximation is proposed for calculating the quasi-dc currents produced in the power system by the surface electric fields. Identification of the processes causing the geomagnetic perturbations responsible for SIC would be aided by investigation of the local time dependence of SIC occurrence. Such knowledge could potentially be used to provide several hours warning of SIC.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Solar-Terrest. Predictions Proc., Vol. 2; p 149-161
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  • 91
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    Magnetic storm effects in electric power systems and prediction needs (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Geomagnetic field fluctuations produce spurious currents in electric power systems. These currents enter and exit through points remote from each other. The fundamental period of these currents is on the order of several minutes which is quasi-dc compared to the normal 60 Hz or 50 Hz power system frequency. Nearly all of the power systems problems caused by the geomagnetically induced currents result from the half-cycle saturation of power transformers due to simultaneous ac and dc excitation. The effects produced in power systems are presented, current research activity is discussed, and magnetic storm prediction needs of the power industry are listed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Solar-Terrest. Predictions Proc., Vol. 2; p 137-148
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  • 92
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    Solar-induced variations of environment affecting manned space flight and spacecraft operations (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Estimates of short and long term solar activity are required for calculating variations in the environment with regard to spacecraft charging, radiation effects, and orbital lifetime. Correlations appear to exist between the time of solar activity and the time of operational anomalies due to electrical discharges when the dielectric surfaces of geosynchronous spacecraft are charged by interaction with the ambient plasma to levels above breakdown voltage. An ability to predict the solar induced variation variability of the plasmas could permit refinement of design criteria. The influence of the radiation on spacecraft materials, systems, and manned operations is summarized. Solar radition effects on the orbital altitude atmospheric density environment and spacecraft lifetimes are also considered.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Solar-Terrest. Predictions Proc., Vol. 2; p 89-103
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  • 93
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    User requirements of solar-terrestrial predictions for spacecraft applications (1979)
    In:  CASI
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    Publication Date: 2006-01-16
    Description: Areas which are influenced by solar-terrestrial coupling effects and which are internal to the Earth's magnetosphere are of interest to mission planners, spacecraft hardware designers, and those engaged in the operation of already orbiting manned or unmanned spacecraft. Accurate models are needed to predict energetic particle flux density, interactions between low energy (10 eV to 100 eV) near-Earth plasma and space systems, and neutral atmospheres. Parameters required for each of these areas are discussed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Marshall Space Flight Center Solar-Terrest. Predictions Proc., Vol. 2; p 1-20
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  • 94
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    Susceptibility of materials processing experiments to low-level accelerations (1981)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: The types of material processing experiments being considered for shuttle can be grouped into four categories: (1) contained solidification experiment; (2) quasicontainerless experiments; (3) containerless experiments; and (4) fluids experiments. Low level steady acceleration, compensated and uncompensated transient accelerations, and rotation induced flow factors that must be considered in the acceleration environment of a space vehicle whose importance depends on the type of experiment being performed. Some control of these factors may be exercised by the location and orientation of the experiment relative to shuttle and by the orbit vehicle attitude chosen for mission. The effects of the various residual accelerations can have serious consequence to the control of the experiment and must be factored into the design and operation of the apparatus.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Spacecraft Dyn. as Related to Lab. Expt. in Space; p 63-68
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  • 95
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    Crystal study and econometric model (1975)
    In:  CASI
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    Publication Date: 2006-04-10
    Description: An econometric model was developed that can be used to predict demand and supply figures for crystals over a time horizon roughly concurrent with that of NASA's Space Shuttle Program - that is, 1975 through 1990. The model includes an equation to predict the impact on investment in the crystal-growing industry. Actually, two models are presented. The first is a theoretical model which follows rather strictly the standard theoretical economic concepts involved in supply and demand analysis, and a modified version of the model was developed which, though not quite as theoretically sound, was testable utilizing existing data sources.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Econ. Analysis of Materials Processing in Space; p 191-233
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  • 96
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    Turbine blade processing (1975)
    In:  CASI
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    Publication Date: 2006-04-10
    Description: Space processing of directionally solidified eutectic-alloy type turbine blades is envisioned as a simple remelt operations in which precast blades are remelted in a preformed mold. Process systems based on induction melting, continuous resistance furnaces, and batch resistance furnaces were evaluated. The batch resistance furnace type process using a multiblade mold is considered to offer the best possibility for turbine blade processing.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Econ. Analysis of Materials Processing in Space; p 91-158
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  • 97
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    Preliminary model for high-power-waveguide arcing and arc protection (1978)
    In:  CASI
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    Publication Date: 2006-01-12
    Description: The arc protection subsystems that are implemented in the DSN high power transmitters are discussed. The status of present knowledge about waveguide arcs is reviewed in terms of a simple engineering model. A fairly general arc detection scheme is also discussed. Areas where further studies are needed are pointed out along with proposed approaches to the solutions of these problems.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Deep Space Network; p 118-125
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  • 98
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    Extraterrestrial fiberglass production using solar energy (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: A conceptual design is presented for fiberglass production systems in both lunar and space environments. The raw material, of lunar origin, will be plagioclase concentrate, high silica content slag, and calcium oxide. Glass will be melted by solar energy. The multifurnace in the lunar plant and the spinning cylinder in the space plant are unique design features. Furnace design appears to be the most critical element in optimizing system performance. A conservative estimate of the total power generated by solar concentrators is 1880 kW; the mass of both plants is 120 tons. The systems will reproduce about 90 times their total mass in fiberglass in 1 year. A new design concept would be necessary if glass rods were produced in space.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Ames Res. Center Space Resources and Space Settlements; p 225-232
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  • 99
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    Exciter switch (1975)
    In:  CASI
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    Publication Date: 2006-01-12
    Description: A new exciter switch assembly has been installed at the three DSN 64-m deep space stations. This assembly provides for switching Block III and Block IV exciters to either the high-power or 20-kW transmitters in either dual-carrier or single-carrier mode. In the dual-carrier mode, it provides for balancing the two drive signals from a single control panel located in the transmitter local control and remote control consoles. In addition to the improved switching capabilities, extensive monitoring of both the exciter switch assembly and Transmitter Subsystem is provided by the exciter switch monitor and display assemblies.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: The Deep Space Network; p 148-183
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  • 100
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    Mutual assistance in space (1975)
    In:  CASI
    Details
    Publication Date: 2006-01-11
    Description: Operating principles, system functions, and technological problems associated with developing compatible spacecraft, station approach, and docking facilities between the U.S. and the U.S.S.R. are reported. Two designs, the probe cone and the androgynous docking device are examined.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Mod. Achievements of Cosmonautics (NASA-TT-F-16221); p 20-38
    Format: text
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