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  • Other Sources  (3,126)
  • MECHANICAL ENGINEERING  (1,586)
  • ASTRONAUTICS (GENERAL)  (1,540)
  • 1980-1984  (1,548)
  • 1975-1979  (1,578)
  • 1945-1949
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  • Other Sources  (3,126)
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Years
Year
  • 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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    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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  • 3
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    Impact tensile testing of wires (1976)
    In:  CASI
    Details
    Publication Date: 2006-08-09
    Description: The test consists of fixing one end of a wire specimen and allowing a threaded falling weight to strike the other. Assuming the dynamic stress in the wire to be a function only of its strain, energy considerations show for negligible wire inertia effects that the governing dynamic stress-strain law can be determined directly from impact energy vs. wire elongation data. Theoretical calculations are presented which show negligible wire inertia effects for ratios of wire mass to striking mass of the order of .01 or less. The test method is applied to soft copper wires and the dynamic stress-strain curve so determined is found to be about 30 percent higher than the corresponding static curve.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Langley Res. Center Advan. in Eng. Sci., Vol. 1; p 319-326
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  • 4
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    Numerical determination of the transmissibility characteristics of a squeeze film damped forced vibration system (1976)
    In:  CASI
    Details
    Publication Date: 2006-08-09
    Description: Numerical solutions of the governing equations of motion of a liquid squeeze film damped forced vibration system were carried out to examine the feasibility of using a liquid squeeze film to cushion and protect large structures, such as buildings, located in areas of high seismic activity. The mathematical model used was that for a single degree of freedom squeeze film damped spring mass system. The input disturbance was simulated by curve fitting actual seismic data with an eleventh order Lagranging polynomial technique. Only the normal component of the seismic input was considered. The nonlinear, nonhomogeneous governing differential equation of motion was solved numerically to determine the transmissibility over a wide range of physical parameters using a fourth-order Runge-Kutta technique. It is determined that a liquid squeeze film used as a damping agent in a spring-mass system can significantly reduce the response amplitude for a seismic input disturbance.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Langley Res. Center Advan. in Eng. Sci., Vol. 1; p 327-338
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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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    Experimental investigation of dynamic characteristics of turbine generators and low-tuned foundations (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: Turbine generator (T-G) units with low tuned concrete foundations were investigated experimentally during both startup and normal operating conditions. The dynamic response of the turbine generators and their foundation systems were characterized by resonance curves obtained during the startup transient and by vibration mode shapes at the normal operating condition. No severe resonance at the fundamental frequencies of the system was observed. The deflection or displacement of the foundation pedestal does not lead to unacceptable T-G vibration. The experimental results are compared and discussed with some previous theoretical studies.
    Keywords: MECHANICAL ENGINEERING
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., Pt. 3; p 69-77
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  • 29
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    Evaluation of rotor-bearing system dynamic response to unbalance (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-02
    Description: The vibration environment within air conditioner rotating machinery referred to as an air cycle machine (ACM) was investigated to effectively increase ACM reliability. To assist in the selection of design changes which would result in improved ACM performance, various design modifications were incorporated into a baseline ACM configuration. For each design change, testing was conducted with the best balance achieveable (baseline) and with various degrees of unbalance. Relationships between unbalance (within the context of design changes) and the parameters associated with design goals were established. The results of rotor dynamics tests used to establish these relationships are presented.
    Keywords: MECHANICAL ENGINEERING
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., Pt. 3; p 41-53
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  • 30
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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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  • 31
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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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  • 32
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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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  • 33
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    Improved techniques of parallel gap welding and monitoring (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Welding programs which show that parallel gas welding is a reliable process are discussed. When monitoring controls and nondestructive tests are incorporated into the process, parallel gap welding becomes more reliable and cost effective. The panel fabrication techniques and the HAC thermal cycling test indicate reliable product integrity. The design and building of automated tooling and fixturing for welding are discussed.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Lewis Research Center Space Photovoltaic Res. and Technol. 1983; p 228-234
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  • 34
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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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  • 35
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    Tribology (1982)
    In:  CASI
    Details
    Publication Date: 2006-04-12
    Description: The adhesion, friction, and wear properties of materials are reviewed and some of the factors influencing these properties are discussed. The forms of lubrication and types of lubricants will also be discussed.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Langley Research Center Advan. Mater. Technol.; p 391-410
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  • 36
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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
    Details
    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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  • 38
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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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  • 39
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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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  • 40
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    Incipient failure detection (IFD) of SSME ball bearings (1982)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Because of the immense noise background during the operation of a large engine such as the SSME, the relatively low level unique ball bearing signatures were often buried by the overall machine signal. As a result, the most commonly used bearing failure detection technique, pattern recognition using power spectral density (PSD) constructed from the extracted bearing signals, is rendered useless. Data enhancement techniques were carried out by using a HP5451C Fourier Analyzer. The signal was preprocessed by a Digital Audio Crop. DAC-1024I noise cancelling filter in order to estimate the desired signal corrupted by the backgound noise. Reference levels of good bearings were established. Any deviation of bearing signals from these reference levels indicate the incipient bearing failures.
    Keywords: MECHANICAL ENGINEERING
    Type: Alabama Univ. in Huntsville The 1981 NASA(ASEE Summer Fac. Fellowship Program; 20 p
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  • 41
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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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  • 42
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    A clamp mechanism for deployable three-ton payloads (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The requirements, capabilities, and unique design features of the instrument payload subsystem payload clamp assembly (PCA) are presented. The PCA is designed to have the flexibility to accommodate a wide payload range varying from 0.5 m to 3 m in diameter and from 500 kg to 3000 kg mass. This is achieved by modular clamp design in connection with replaceable struts. The design features include clamping of payload in a statically determined way and actuation of clamp latches by means of single linear actuator via ropes. The vibration and TV environmental conditions for the mechanism are extremely severe. A structural and prototype model was built. Test results of the operating characteristic are presented. In addition, problems of tribology are highlighted.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 375-390
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  • 43
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    An antenna pointing mechanism for large reflector antennas (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: An antenna pointing mechanism for large reflector antennas on direct broadcasting communication satellites was built and tested. After listing the requirements and constraints for this equipment the model is described, and performance figures are given. Futhermore, results of the qualification level tests, including functional, vibrational, thermovacuum, and accelerated life tests are reported. These tests were completed successfully.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 253-261
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  • 44
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    A drive unit for the instrument pointing system (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: The requirements, capabilities, and unique design features of the instrument pointing system drive units (DU) are presented. The DU's are identical for all three gimbal axes (elevation, cross elevation, and azimuth) and provide alternating rotation of shaft versus the housing of + or - 180 deg. The design features include: two ball bearing cartridges using cemented carbide balls coated with TiC a layer; redundant brushless torque motors and resolvers; a load by-pass mechanism driven by a dc torque motor to off-load the bearings during ascent/descent, ground transportation, and to provide an emergency breaking capability; and cabling over each gimbal axis by means of cable follow-up consisting of 13 signal and 15 power flat band cable loops. Test results of disturbance torque characteristics are presented.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 263-278
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  • 45
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    An antenna fine pointing mechanism (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: SOFA, a device designed for the highly accurate 2 axis pointing of antenna or any feature installed on a spacecraft is described. The major characteristic of this system is complete freedom from friction and wear out, resulting in numerous advantages, such as outstanding precision, virtually endless service life, high simplicity, and reliability. The sizing method is described and performances are analyzed. The results from analogue simulations are presented. A functional model of the electrical and mechanical parts was built and subjected to on ground tests using a 2 axis platform simulating the spacecraft's motions. The results obtained are thoroughly in keeping with the predictions and simulations. Various possible applications of the SOFA system are mentioned.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 235-252
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  • 46
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    A mechanical drive for retractable telescopic masts (1981)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: Test results on the mechanical drive have indicated that the system is capable of deploying a typical telescopic mast under ambient conditions. The design can be considered for a wide range of space applications since, in theory, there is no limit to the number of tubes that can be deployed. The mechanical system offers a number of advantages over a gas driven system, such as the ability to retract and also provide a significant mass saving.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center The 15th Aerospace Mech. Symp.; p 205-217
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  • 47
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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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  • 48
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    Skylab: A beginning (1977)
    In:  CASI
    Details
    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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  • 49
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    A survey of Rocketry and astronautics in Spain (1977)
    In:  CASI
    Details
    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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  • 50
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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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  • 51
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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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  • 52
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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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  • 53
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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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  • 54
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    Test evaluation of shock buffering concept for hydrodynamic ram induced by yawing projectile impacting a simulated integral fuel tank (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: A concept for containing the shock inputs due to hydrodynamic ram caused by an impacting projectile within a fuel cell is discussed. This is to provide a buffering layer of foam, flexible, rigid or a combination thereof, which is sealed from the liquid. A program is described in which this buffering concept was tested. The effectiveness of a novel muzzle-mounted, 'tumble', test device is shown.
    Keywords: MECHANICAL ENGINEERING
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., Pt. 1; p 141-170
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  • 55
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    Guido von Pirquet: Austrian pioneer of astronautics (1977)
    In:  CASI
    Details
    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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  • 56
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    Progress Report on Project Mercury (1976)
    In:  CASI
    Details
    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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  • 57
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    Guidelines for advanced manned space vehicle program, June 1960 (1976)
    In:  CASI
    Details
    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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  • 58
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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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  • 59
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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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  • 60
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    Mass drivers. 3: Engineering (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: The last of a series of three papers by the Mass-Driver Group of the 1977 Ames Summer Study is presented. It develops the engineering principles required to implement the basic mass-driver. Optimum component mass trade-offs are derived from a set of four input parameters, and the program used to design a lunar launcher. The mass optimization procedures is then incorporated into a more comprehensive mission optimization program called OPT-4, which evaluates an optimized mass-driver reaction engine and its performance in a range of specified missions. Finally, this paper discusses, to the extent that time permitted, certain peripheral problems: heating effects in buckets due to magnetic field ripple; an approximate derivation of guide force profiles; the mechanics of inserting and releasing payloads; the reaction mass orbits; and a proposed research and development plan for implementing mass drivers.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Ames Res. Center Space Resources and Space Settlements; p 119-157
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  • 61
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    Mass drivers. 1: Electrical design (1979)
    In:  CASI
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    Publication Date: 2006-01-12
    Description: A mass driver is an electrical device used to accelerate payloads of any material to a high velocity. Small vehicles (called buckets) containing superconducting coils carry the payloads. These buckets are accelerated by pulsed magnetic fields, timed by information on their position, and are guided by induced magnetic fields set up in a surrounding guideway. Upon reaching the correct velocity, the buckets release their payloads, then they are slowed for recirculation to be reused. A rationale is presented that leads to a relatively simple and near-optimum design, as well as basic programs for calculating acceleration. The transverse oscillation frequencies are found to be invariant to guideway transverse dimensions.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Ames Res. Center Space Resources and Space Settlements; p 87-100
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  • 62
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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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  • 63
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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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  • 64
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    User requirements of solar-terrestrial predictions for spacecraft applications (1979)
    In:  CASI
    Details
    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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  • 65
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    Tribology experiment (1981)
    In:  CASI
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    Publication Date: 2006-02-14
    Description: A two-dimensional concept for Spacelab rack 7 was developed to study the interaction of liquid lubricants and surfaces under static and dynamic conditions in a low-gravity environment fluid wetting and spreading experiments of a journal bearing experiments, and means to accurately measure and record the low-gravity environment during experimentation are planned. The wetting and spreading process of selected commercial lubricants on representative surface are to the observes in a near-zero gravity environment.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Marshall Space Flight Center Spacecraft Dyn. as Related to Lab. Expt. in Space; p 58-60
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  • 66
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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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  • 67
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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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    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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  • 69
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    An experimental design for total container impact response modeling at extreme temperatures (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-16
    Description: An experimental design (a drop test) was developed to test the effects of confinement upon cushions. The drop test produced consistent corner void cushion data from which mathematical models were developed. A mathematical relationship between temperature and drop height was found.
    Keywords: MECHANICAL ENGINEERING
    Type: Shock and Vibration Inform. Center The Shock and Vibration Bull., Pt. 1; p 101-107
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  • 70
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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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  • 71
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    Mass drivers. 2: Structural dynamics (1979)
    In:  CASI
    Details
    Publication Date: 2006-01-12
    Description: Various structural and dynamical problems related to both small-scale forces between the drive coils and within the bucket structure as well as the overall combined large-scale dynamical interaction of the bucket stream and MDRE (Mass Drive Reaction Engine) structure are examined. The large-scale dynamics appear weakly stable. Finally, MDRE operation in an inverse-square-law gravitational field is discussed and the required curved shape of the guideway is computed.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA. Ames Res. Center Space Resources and Space Settlements; p 101-118
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  • 72
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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
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  • 73
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    Minimum energy control of a class of electrically driven vehicles (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: Theoretical and experimental results are obtained in the investigation of a minimum energy control problem associated with a class of electrically driven vehicles. Analytical results are obtained by making several justifiable approximations in the dynamical equations of the plant, the performance index of which is related to the minimization of system energy consumption for any required control action. The control problem of interest is simplified and solved by using Bellman's invariant imbedding technique. The optimality of the resulting control law is compared with those of the bang-bang control law, which is the exact solution for the case of speed-setting control action, and the classical control laws under identical conditions. A stochastic optimization problem is then formulated and solved by using Bellman's dynamic programming technique. The resulting control law is mechanized for a particular vehicle configuration which is simulated in the laboratory.
    Keywords: MECHANICAL ENGINEERING
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 387-421
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  • 74
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    Introduction to Long-Duration Exposure Facility (1984)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A description of the structure and uses of the Long Duration Exposure Facility (LDEF) is given. The LDEF was designed to provide a large number of economical opportunities for science and technology experiments that require modest electrical power and data processing while in space and which benefit from postflight laboratory investigations with the retrieved experiment hardware. Like the Shuttle, the LDEF is reusable, and repeat missions are planned, each with a new complement of experiments. The LDEF is essentially a free-flying cylindrical structure. The experiments on LDEF are totally self-contained in trays mounted on the exterior of the structure. LDEF can accommodate 86 experiment trays, 72 around the circumference and 14 on the two ends. The LDEF is delivered to Earth orbit by the Shuttle. In orbit, the Shuttle remote manipulator system removes the LDEF from the Shuttle payload bay and places it in a gravity-gradient-stabilized attitude. After an extended period in orbit, which is set by experiment requirements, the LDEF is retrieved on a subsequent Shuttle flight.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: NASA. Langley Research Center Long Duration Exposure Facility (LDEF); p 1-5
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  • 75
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    The processing of semiconductor materials (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-06
    Description: Five experiments involving the processing of semiconductor materials were performed during the Skylab mission. After discussions on semiconductors and their unique electronic properties, and techniques of crystal growth, these five experiments are presented. Four melt growth experiments were attempted: (1) steady state growth and segregation under zero gravity (InSb); (2) seeded, containerless solidification of InSb; (3) influence of gravity-free solidification on microsegregation; and (4) directional solidification of InSb-GaSb alloys. One vapor growth experiment, crystal growth by vapor transport, was attempted.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Early Space Expt. in Mater. Process.; 45 p
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  • 76
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    The promise of space processing (1979)
    In:  CASI
    Details
    Publication Date: 2006-07-06
    Description: The long exposure to a virtually zero-gravity environment is a truly unique situation that cannot be duplicated or even approximated for any length of time on earth. The topics discussed are: (1) low gravity; (2) atmospheric effects; (3) potential advantages of materials processing in space; (4) the absence of buoyancy-driven convection; (5) the absence of hydrostatic pressure; (6) the absence of sedimentation and buoyancy; (7) containerless processing; and (8) ultrahigh vacuum processing.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Early Space Expt. in Mater. Process.; 37 p
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  • 77
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    Summary and recommendations (1975)
    In:  CASI
    Details
    Publication Date: 2006-04-10
    Description: An economic analysis using econometric and cost benefit analysis techniques was performed to determine the feasibility of space processing of certain products. The overall objectives of the analysis were (1) to determine specific products or processes uniquely connected with space manufacturing, (2) to select a specific product or process from each of the areas of semiconductors, metals, and biochemicals, and (3) to determine the overall price/cost structure of each product or process considered. The economic elements of the analysis involved a generalized decision making format for analyzing space manufacturing, a comparative cost study of the selected processes in space vs. earth manufacturing, and a supply and demand study of the economic relationships of one of the manufacturing processes. Space processing concepts were explored. The first involved the use of the shuttle as the factory with all operations performed during individual flights. The second concept involved a permanent unmanned space factory which would be launched separately. The shuttle in this case would be used only for maintenance and refurbishment. Finally, some consideration was given to a permanent manned space factory.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Econ. Analysis of Materials Processing in Space; p 234-251
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  • 78
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    Economic analysis of materials processing in space: Introduction (1975)
    In:  CASI
    Details
    Publication Date: 2006-04-10
    Description: Space processing concepts investigated included an unmanned space factory, and a permanently launched factory. Product lines chosen for analysis were: (1) turbine blades, (2) tungsten targets for X-ray machines, (3) 1 sub G subclass separation by electrophoresis, and (4) high-price exotic crystals. The turbine blade, and 1 sub G products are considered promising candidates.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Econ. Analysis of Materials Processing in Space; p 1-7
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  • 79
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    Robotic fruit harvester (1982)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: MECHANICAL ENGINEERING
    Type: NASA Technol. Appl. Team; p 15
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  • 80
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    Man in space - A time for perspective (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Factors affecting crew performances in long-term space flights are examined with emphasis on the Space Shuttle-Spacelab program. Biomedical investigations carried out during four Skylab missions indicate that initially rapid changes in certain physiological parameters, notably in cardiovascular response and red-blood-cell levels, lead to an adapted condition. Calcium loss remains a potential problem. Space Shuttle environmental control and life-support systems are described together with technology facilitating performance of mission objectives in a weightless environment. It is concluded that crew requirements are within the physical and psychological capability of astronauts, but the extent to which nonastronaut personnel will be able to participate without extensive training and pre-conditioning remains to be determined.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Astronautics and Aeronautics; 13; Oct. 197
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  • 81
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    What is EHD (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The life of many highly loaded machine elements relies on the formation of a very thin elastohydrodynamic (EHD) oil film between surfaces in motion. Its formation results from the combination of a remarkable set of circumstances rarely appreciated. This article endeavors to explain the mechanism of elastohydrodynamic lubrication with simple physical concepts that are easy to understand.
    Keywords: MECHANICAL ENGINEERING
    Type: Lubrication Engineering; 31; June 197
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  • 82
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    Man's future in space (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Studies evaluating potential operational and commercial uses of space are being conducted, taking into account astronomy, astrophysics, manned bases and laboratories in earth orbit, space colonization, terrestrial communications, space processing and manufacturing, interstellar probes, planetary exploration, and the use of space for terrestrial energy supply. The present status in the exploration of the solar system is examined, giving attention to Jupiter, Venus, Mars, and Mercury. A brief outline of the development of human colonies on Mars is presented.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Spaceflight; 17; Mar. 197
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  • 83
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    Time bases, discretes, and interrupts (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The effort performed to assure proper flight program handling of time bases, discretes, and interrupts was discussed. The following time bases are used as key mission events: guidance reference release, liftoff, S-1B low level sensors dry, S-1B outboard engines cutoff, S-IVB cutoff, and S-IVB de-orbit DCS command. The five discrete outputs in the discrete output register were verified for proper setting. Each discrete input is honored in the proper time frame by forcing each discrete in the following intervals: before the discrete is enabled, after the discrete has been detected, and after the discrete has been disabled. As an assurance that an interrupt is honored only in the proper time frames, each interrupt was forced during the following intervals: prior to the specified enable time, after the interrupt has been honored, after the interrupt has been disabled.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Program Verification Doc. for the ASTP Flight Program; 10 p
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  • 84
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    Utilization of the vacuum developed in the wake zone of space vehicles in the LDEF class (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Contaminating fluxes from upper atmospheric molecules found in the wake of a typical spacecraft of the Long Duration Exposure Facility class are studied with the aim of determining vacuum levels which may be employed by experiments mounted on the vehicle. A simplified representation for the spacecraft, the velocity-shifted Maxwellian distribution (to evaluate ambient flux which has a velocity sufficient to overtake the spacecraft), and a calculation for the backscattered contribution to the flux density of the wake figure in the study are presented. Results indicate that direct and backscattered fluxes of about 10 to the seventh power molecules per sq cm can be expected in the wake of a spacecraft at 550 km altitude.
    Keywords: ASTRONAUTICS (GENERAL)
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  • 85
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    Orbiting molecular-beam laboratory (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The composition of the atmosphere within the planned orbital envelope of the Space Shuttle and the velocity necessary to maintain a stable orbit within that envelope provide unique conditions for forming a high-purity, moderate energy beam (about 5 eV) of atomic oxygen. At 500 km, for example, atomic oxygen comprises approximately 90% of the atmosphere. Since the mean thermal speed of the ambient atomic oxygen is substantially less than the orbital speed, a high-purity beam can be generated by sweeping through the gas with a series of beam-forming truncated conical shells. Characteristics of the beam, including energy distribution, flux, and purity variation with orbital altitude and methods for lowering the mean energy, are presented. Gas-surface interaction experiments that have been proposed for this laboratory are also discussed.
    Keywords: ASTRONAUTICS (GENERAL)
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  • 86
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    On humanity's role in space (1978)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Manned spaceflight is considered within the framework of two broad categories: human exploitation of space for economic or scientific gain, and human habitation of space as a place where man may live, grow, and actualize himself. With the advent of the Space Shuttle, exploitation of space will take the form of new product development. This will continue during the 1990s as the new products are manufactured on a scale large enough to be profitable. The turn of the century should see major industries in space, and large space habitats. Thus, the question of mankind's existential needs arises. In addition to basic physical needs, the spiritual and cultural requirements of human beings must be considered. The impact of man's presence in space upon human culture in general is discussed with reference to international cooperation, public interest in space programs, scientific advancement, the basic urge to explore, and the density of mankind as a whole; which will become free of external constraints as we step into the cosmos.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Spaceflight; 20; Feb. 197
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  • 87
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    International Sun-Earth Explorer - A three-spacecraft program (1977)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The International Sun-Earth Explorer (ISEE) is a three-spacecraft system developed by NASA and ESA to study the magnetospheric structure, paying attention to the quantitative mechanism of magnetospheric response to external perturbations, and the structure of its parts. In particular, the nature, structure, motion, and stability of magnetospheric boundaries will be studied, including bow shock, magnetopause, plasmapause, and neutral sheet. Spacecraft ISEE-A and ISEE-B will be launched into the same orbit (of apogee 23 earth radii) but separated by a small, controllable distance, and will make observations from within the magnetosphere. The ISEE-C spacecraft will be launched into a heliocentric orbit (234 earth radii upstream) and will make observations in the solar wind upstream of the earth.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Science; 198; Oct. 14
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  • 88
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    Variable polarity plasma arc welding on the Space Shuttle external tank (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Variable polarity plasma arc (VPPA) techniques used at NASA's Marshall Space Flight Center for the fabrication of the Space Shuttle External Tank are presentedd. The high plasma arc jet velocities of 300-2000 m/s are produced by heating the plasma gas as it passes through a constraining orifice, with the plasma arc torch becoming a miniature jet engine. As compared to the GTA jet, the VPPA has the following advantages: (1) less sensitive to contamination, (2) a more symmetrical fusion zone, and (3) greater joint penetration. The VPPA welding system is computerized, operating with a microprocessor, to set welding variables in accordance with set points inputs, including the manipulator and wire feeder, as well as torch control and power supply. Some other VPPA welding technique advantages are: reduction in weld repair costs by elimination of porosity; reduction of joint preparation costs through elimination of the need to scrape or file faying surfaces; reduction in depeaking costs; eventual reduction of the 100 percent-X-ray inspection requirements. The paper includes a series of schematic and block diagrams.
    Keywords: MECHANICAL ENGINEERING
    Type: Welding Journal (ISSN 0043-2296); 63; 27-35
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  • 89
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    The growth of materials processing in space - A history of government support for new technology (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Development of a given technology for national defense and large systems developments when the task is too large or risky for entrepreneurs, yet is clearly in the best interest of the nation are discussed. Advanced research to identify areas of interest was completed. Examples of commercial opportunities are the McDonnell-Douglas Corporation purification process for pharmaceutical products and the Microgravity Research Associates process for growing gallium arsenide crystals in space.
    Keywords: ASTRONAUTICS (GENERAL)
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  • 90
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    Containerless processing technology (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A partial description of the technology, hardware, and facilities developed by NASA in support of space-based containerless processing experiments in the early 1970s is presented, along with recent results. Supercooling was necessary, at a rate of 500 K over a 400 ft span, in early drop tower and molten sample experiments. Placing an electromagnetic levitation coil/chamber at the top of the tube avoided contamination of the sample by guide wires. Recent tests have been performed in attempts to produce metastable bulk A-15 Nb3Ge. The use of copper coils for levitation is suspected to have induced stirring motions in samples. Aerodynamic levitation, needed for nonconducting materials, has been employed to process glass beads at temperatures over 1000 K. An electromagnetic levitation device used to process a gram of BeO on a sounding rocket flight will be carried on a Shuttle flight, as will an acoustic suspension system.
    Keywords: ASTRONAUTICS (GENERAL)
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  • 91
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    Payload crew members' view of Spacelab operations (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Various operational aspects of the Spacelab 1 mission are reviewed by the four payload crew members. Two-shift operations, voice communication with ground investigators, joint participation in experiment activity, Spacelab performance, and recent advances are discussed.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Science (ISSN 0036-8075); 225; 165-167
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  • 92
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    Two-phase turbine staging (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Two-phase turbines would be useful in Rankine cycles using low-quality or saturated-liquid working fluids. The chief problem is low efficiency due to slip losses in nozzles and due to liquid impact and friction losses in rotors. To raise efficiency, a staging method was tested in which the first stage operated at high speed with low relative liquid velocity, and the second stage recovered the first-stage exit energy. The theoretical efficiency for an experimental turbine operating with Refrigerant-22 was raised from 55 percent to 66 percent, and the measured efficiency was raised from 52 percent to 57 percent.
    Keywords: MECHANICAL ENGINEERING
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  • 93
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    DOE/NASA Automotive Stirling Engine Project Overview 83 (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An overview of the DOE/NASA Automotive Stirling Engine Project is presented. The background and objectives of the project are reviewed. Project activities are described and technical progress and status are presented and assessed. Prospects for achieving the objective 30 percent fuel economy improvement are considered good. The key remaining technology issues are primarily related to life, reliability and cost, such as piston rod seals, and low cost heat exchanges. Previously announced in STAR as N83-27924
    Keywords: MECHANICAL ENGINEERING
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  • 94
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    An analysis of temperature effect in a finite journal bearing with spatial tilt and viscous dissipation (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The analysis presented herein deals with the evaluation of the pressure, velocity, and temperature profiles in a finite-length plane journal bearing. The geometry of the case under study consists of a spatially tilted shaft. The two-dimensional Reynolds equation accounts for the variation of the clearance gap h with x and z and is used to model the pressure field. The latter is solved for a variety of shaft tilt angles and then used to calculate the two-dimensional flow field. Finally, the flow field is used in the energy equation to solve for the film temperature profile, when the effect of viscous dissipation is taken into account.
    Keywords: MECHANICAL ENGINEERING
    Type: ASLE Transactions; 27; 405-412;
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  • 95
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    Influence of unbalance on the nonlinear dynamical response and stability of flexible rotor-bearing systems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: In this paper, some of the effects of unbalance on the nonlinear response and stability of flexible rotor-bearing systems is presented from both a theoretical and experimental standpoint. In a linear system, operating above its stability threshold, the amplitude of motion grows exponentially with time and the orbits become unbounded. In an actual system, this is not necessarily the case. The actual amplitudes of motion may be bounded due to various nonlinear effects in the system. These nonlinear effects cause limit cycles of motion. Nonlinear effects are inherent in fluid film bearings and seals. Other contributors to nonlinear effects are shafts, couplings and foundations. In addition to affecting the threshold of stability, the nonlinear effects can cause jump phenomena to occur at not only the critical speeds, but also at stability onset or restabilization speeds.
    Keywords: MECHANICAL ENGINEERING
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  • 96
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    Ceramics potential in automotive powerplants (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The paper addresses the potential that ceramic materials can play an important role in future automotive powerplants - both advanced heat engines and advanced battery systems. A number of related experimental programs are reviewed including ceramics for gasoline and diesel piston engines, gas turbine and Stirling Engines and sodium-sulfur batteries. A strong integrated program to develop ceramics technology is recommended.
    Keywords: MECHANICAL ENGINEERING
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  • 97
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    Dendritic solidification in a binary alloy melt: Steady-state versus morphological stability theories (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A model for dendritic growth in a binary alloy melt, in the presence of a positive temperature gradient in the liquid, is presented. The model describes satisfactorily the transition from a dendritic interface to a planar interface at very low and very large growth rates. A dendrite tip stability parameter is derived, strictly from steady state considerations, without resorting to a perturbation analysis. The estimates of the parameter agree with those obtained by models based on perturbation analyses.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Fifth European Symp. on Mater. Sci. under Microgravity. Results of Spacelab 1; p 403-407
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  • 98
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    Crystal growth of GaAs in space (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: It is shown that stoichiometry variations in the GaAs melt during growth constitute the most critical parameter regarding defect formations and their interactions; this defect structure determines all relevant characteristics of GaAs. Convection in the melt leads to stoichiometric variations. Growth in axial magnetic fields reduces convection and permits the study of defect structure. In order to control stoichiometry in space and to accommodate expansion during solidification, a partially confined configuration was developed. A triangular prism is employed to contain the growth melt. This configuration permits the presence of the desired vapor phase in contact with the melt for controlling the melt stoichiometry.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: ESA Fifth European Symp. on Mater. Sci. under Microgravity. Results of Spacelab 1; p 221-225
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  • 99
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    Electromagnetic containerless undercooling facility and experiments for the Shuttle (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An electromagnetic furnace is being prepared for flights aboard the Space Shuttle. This apparatus is capable of melting metals and alloys up to 1400 C melting point by induction heating with subsequent solidification of the freely levitated melt without contact with any container. The solidification can be carried out with greatly reduced fields resulting in minimal heating and stirring of the free melt. Sequential specimens can be processed during flight. Several experiments are planned for a series of flights, beginning in 1985 with an undercooling experiment of NiSn alloys. These will be interspersed with detailed studies of fluid flow caused by low and high field levels in order to quantify the corresponding effect upon the solidification process.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Advances in Space Research (ISSN 0273-1177); 4; 5, 19; 99-103
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  • 100
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    Into mesh lubrication of spur gears with arbitrary offset oil jet. I - For jet velocity less than or equal to gear velocity (1983)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An analysis was conducted for into mesh oil jet lubrication with an arbitrary offset and inclination angle from the pitch point for the case where the oil jet velocity is equal to or less than pitch line velocity. The analysis includes the case for the oil jet offset from the pitch point in the direction of the pinion and where the oil jet is inclined to intersect the common pitch point. Equations were developed for the minimum oil jet velocity required to impinge on the pinion or gear and the optimum oil jet velocity to obtain the maximum impingement depth.
    Keywords: MECHANICAL ENGINEERING
    Type: ASME; 713-718
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