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  • Weitere Quellen  (791)
  • PROPULSION SYSTEMS  (323)
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  • 1
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    Metal-silicate friction in ultrahigh vacuum (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Results of the analysis and experiments on the frictional behavior of materials under conditions of ultrahigh vacuum, as related to kinematic problems in a lunar environment, are presented. Experiments have been performed under varying conditions of cleanliness to determine frictional characteristics at 10 to the minus 7th power to 10 to the minus 8th power torr between flat basalt and spherical 7075-T6 aluminum surfaces. A quantitative analysis has been made of the factors influencing frictional behavior of these materials. The proposed mathematical model incorporated parameters of surface cleanliness, surface roughness, and surface energy.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 149-156
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  • 2
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    Accelerated vacuum testing of long life ball bearings and sliprings (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Extensive analytical studies and testing have been conducted on bearings and sliprings in vacuum at temperatures from 30 to 130 F. Thirty-six bearings lubricated with two types of oil were tested in vacuum of less than 10 to the minus 8th power torr at speeds from 55 to 180 rpm. Temperatures, load, speed, and oil viscosity were varied to evaluate the effects on life and wear. All bearings performed successfully during a 7-month test, and the potential merits of the two oils were compared. Over 25 different, dry-lubricated brush/slipring material combinations have been tested, with variations of brush and ring design and surface speed. Test results indicate the probability of 10 years or more of slipring and brush lifetime with properly designed brushes for 1-in.-diameter ring rotating at 60 rpm.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 127-135
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  • 3
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    Effects of energy dissipation in the bearing assemblies of dual-spin spacecraft (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Proper evaluation of the effects of bearing assembly flexibility on the attitude stability of dual-spin spacecraft may explain the observed anomalies in the motion of a recently launched satellite. A convenient, but approximate, expression with which to gauge these effects is presented, as in an example of a possible application of this expression in a design role.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 143-148
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  • 4
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    Supersonic cruise inlets (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Design and characteristics of supersonic cruise inlets
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 283-312
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  • 5
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    Application of advanced aerodynamics to future transport aircraft (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Applications of supercritical airfoils to transport aircraft designs
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 165-176
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  • 6
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    Aircraft response to the wing trailing vortices generated by large jet transports (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Flight tests for evaluating effect of wing-tip vortex wake generated by large jet transports on smaller aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 115-126
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  • 7
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    Progress report on wing-trailing-vortex studies (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Effect of wing-tip vortex wakes generated by large jet transport aircraft on smaller airplanes
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA AIRCRAFT SAFETY AND OPERATING PROBL., VOL. 1 1971; P 101-113
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  • 8
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    Gust alleviation (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Alleviation of lateral and longitudinal gust effects on aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 505-553
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  • 9
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    Effects of aeroelasticity on static aerodynamic derivatives (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Effects of aeroelasticity on static longitudinal aerodynamic derivatives
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 375-438
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  • 10
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    Design of bodies for low drag and high performance in practical hypersonic flight (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Minimizing drag and increasing performance of optimum shapes at hypersonic flight
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 103-174
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  • 11
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    Methods of obtaining stability derivatives (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-27
    Beschreibung: Least squares method and iteration technique for obtaining aerodynamic stability derivatives
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 71-101
    Format: text
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  • 12
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    Experiment D016: Power tool evaluation (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Power tool evaluation was not attempted during the Gemini 11 mission because of the premature termination of the on-umbilical extravehicular activity (EVA). The experiment had been scheduled for the Gemini 8 mission, but early mission termination prevented completion of the experiment. However, the objective, equipment description, and experimental precedures are described briefly in this report.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: The Gemini Program: Phys. Sci. Expt. Sum.; p 513-522
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  • 13
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    Meeting the challenge of a 50000-hour-life-time requirement (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: Space mission requirements for the 70's have established a 50,000-hour-lifetime challenge for the mechanisms designer. This challenge may be met by two approaches: (1) development of new materials for wear-prone elements, and (2) design innovation of new electromechanical devices that do not include mechanical wear-prone components. Present state-of-the-art materials require restricted operation regarding load, speed, and power for gears, bearings, and brush-slipring components. These restrictions are discussed, and methods of improvement are suggested. The design-innovations approach is discussed and is illustrated by the design of an experimental magnetically suspended motor.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: 5th Aerospace Mech. Symp.; p 159-164
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  • 14
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    A motor canister designed for prolonged operation in space (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: A special canister was designed to protest the dc motors used on the ISIS 1 antenna unit. The canister is provided with a pressure-monitoring device and has a special shaft seal that imparts minimum load to the motor output shaft. The development and flight testing of the canister are discussed. Problems that were encountered during fabrication and inspection and the problems caused by material/lubricant incompatibility and low temperature are also discussed.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 137-142
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  • 15
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    Nutation dampers for single-spin satellites (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: The physical principles, analysis, and some of the design considerations of passive nutation dampers for single-spin satellites are discussed.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: 5th Aerospace Mech. Symp.; p 83-85
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  • 16
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    A release mechanism with mechanical redundancy (1971)
    In:  CASI
    Details
    Publikationsdatum: 2005-11-30
    Beschreibung: A simple release mechanism is described that achieves high reliability through active mechanical redundancy on the SERT 2 satellite. Principle of operation, design details, and the test program are discussed. Examples of developmental and proposed alternate configurations also are included.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA. Goddard Space Flight Center 5th Aerospace Mech. Symp.; p 121-126
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  • 17
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    Advancements in bearings, seals, and lubricants (1971)
    In:  CASI
    Details
    Publikationsdatum: 2009-11-16
    Beschreibung: Development of bearings, seals, and lubricants for air breathing turbojet engines
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: AIRCRAFT PROPULSION 1971; P 421-463
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  • 18
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    Flutter and unsteady lift theory (1971)
    In:  CASI
    Details
    Publikationsdatum: 2009-11-16
    Beschreibung: Aeroelasticity and unsteady flow problems of aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: PERFORMANCE AND DYN. OF AEROSPACE VEHICLES 1971; P 289-374
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  • 19
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    Fan and compressor technology (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Characteristics of fans and compressors for aircraft turbine engines
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 1-36
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  • 20
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    Dynamics and control (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Dynamics and control of supersonic propulsion systems
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 351-395
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  • 21
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    Effects of engine inlet disturbances on engine stall performance (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Effects of engine inlet disturbances on engine stall performance
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 313-341
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  • 22
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    Supersonic exhaust nozzles (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Design and characteristics of exhaust system for supersonic aircraft
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 233-282
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  • 23
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    V/STOL propulsion (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Propulsion technology for STOL and V/STOL commercial aircraft
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 135-168
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  • 24
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    Turbine cooling research (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Development of improved turbine cooling processes and facilities for conducting turbine cooling research
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 57-96
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  • 25
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    Low cost engines for aircraft (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Development and characteristics of low cost engines for general aviation aircraft
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 211-231
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  • 26
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    Combustion (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Effects of engine design and propulsion system configurations on combustion efficiency
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 97-134
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  • 27
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    Turbine aerodynamic considerations for advanced turbines (1971)
    In:  CASI
    Details
    Publikationsdatum: 2006-04-20
    Beschreibung: Aerodynamic characteristics of advanced turbine engines
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AIRCRAFT PROPULSION 1971; P 37-55
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  • 28
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    Injection into a supersonic stream from the windward side of sweptback injectors at angle of attack (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Windward injection into supersonic stream at angle of attack, minimizing vortex disruption
    Schlagwort(e): AERODYNAMICS
    Materialart: ; 394-398. (
    Format: text
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  • 29
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    Viscous slipstream flow downstream of a centerline Mach reflection (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Viscous slipstream flow downstream of triple shock wave intersection in supersonic diffuser air flow, using Pitot and static pressure probe measurements
    Schlagwort(e): AERODYNAMICS
    Materialart: ; - ASTRONOMY 1969- TE
    Format: text
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  • 30
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    Application of a deflagration plasma gun as a space propulsion thruster (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Space propulsion by plasma deflagration gun, measuring specific impulse by piezoelectric probe and pendulum methods
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; YAL SOCIETY (
    Format: text
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  • 31
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    High temperature fastener technology (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Structural fasteners of heat resistant alloys for high temperature applications
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA. MANNED SPACECRAFT CENTER NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 2 APR. 1971; P 585-599
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  • 32
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    An experimental study of the hypersonic aerodynamics of delta wings. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Results of aerodynamic balance and pressure measurements carried out in a hypersonic gun tunnel (at a free-stream Mach number of 8.2 and a Reynolds number of 800,000) on delta wings having sharp leading edges swept at 70 and 76 deg. The experimental force and pressure coefficients and shock angles are discussed in relation to simple prediction methods. Some transition data are also included.
    Schlagwort(e): AERODYNAMICS
    Materialart: Aeronautical Society of India; vol. 23
    Format: text
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  • 33
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    Designing the brawny gas bearing. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Discussion of a graphic technique for matching specific groove parameters to operating conditions in order to optimize the load carrying capacity of a herringbone-grooved bearing. Details are given on the optimization of the film thickness ratio, the groove width ratio, the groove angle, and the groove length ratio to obtain a maximum radial load capacity. The effect of the dimensionless bearing number on optimal groove configuration parameters is shown in diagrams. Curves are also plotted to compare the capacities of a herringbone-grooved bearing and a plain bearing, showing the former has a higher load capacity than the latter when the dimensionless bearing number is large.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: Machine Design; 43; Dec. 23
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  • 34
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    Dye penetrant indications caused by superficial surface defects in 2014 aluminum alloy welds. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Demonstration that dye penetrant indications on the heat-affected zone of 2014-T6 aluminum GMA weldments are frequently caused by superficial surface conditions and are less than 0.007 in. deep. The following methods are suggested for minimization of these surface defects: stabilization of the arc, application of dc ?GTA' welding procedures, reduction of the caustic etch time, and use of fine grain materials.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: Welding Journal; vol. 50
    Format: text
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  • 35
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    Lubrication with sputtered MoS2 films. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Sputtered MoS2 films (2000-6500 A) were deposited on highly polished metal surfaces. These films have a low coefficient of friction (0.03-0.04) at speeds of 40-80 rpm and loads of 250-1000 grams. At loads of 250 grams the wear lives are over 0.5 million cycles, but at 1000 gram loads, it decreases to 38,000 cycles. Friction experiments and tensile tests have indicated that sputtered films have a strong adherence to metal surfaces. Electron transmission, diffraction and scanning electron microscopy show that these films have an extremely small particle size, less than 30 A in diameter, and are very dense and free from observable pinholes. The high kinetic energy of these sputtered species, the submicroscopic particle size and the sputter-etched substrate surface is responsible for strong adhesion and cohesion of the sputtered film.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
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  • 36
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    Sound propagation and absorption in foam - A distributed parameter model. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Liquid-base foams are highly effective sound absorbers. A better understanding of the mechanisms of sound absorption in foams was sought by exploration of a mathematical model of bubble pulsation and coupling and the development of a distributed-parameter mechanical analog. A solution by electric-circuit analogy was thus obtained and transmission-line theory was used to relate the physical properties of the foams to the characteristic impedance and propagation constants of the analog transmission line. Comparison of measured physical properties of the foam with values obtained from measured acoustic impedance and propagation constants and the transmission-line theory showed good agreement. We may therefore conclude that the sound propagation and absorption mechanisms in foam are accurately described by the resonant response of individual bubbles coupled to neighboring bubbles.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: Acoustical Society of America; vol. 50
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  • 37
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    Extension of a perturbation-expansion method to strong-interaction boundary-layer problems, with application to vorticity interaction (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Modified asymptotic perturbation expansion method application to free flow rotation effect on boundary layer for hypersonic flow about blunt body
    Schlagwort(e): AERODYNAMICS
    Materialart: ; 35 (
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  • 38
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    Electrical power systems for space - Achievements and issues (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Electrical power systems for spacecraft, reviewing solar cells, batteries, fuel cells and radioisotope thermoelectric generators
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; 353-366. (
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  • 39
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    A comparative study of three axisymmetric inlets for a hypersonic cruise mission (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Axisymmetric inlet design for turboramjet powered hypersonic cruise vehicle, examining effects of spillage and cowl drags on air flow characteristics
    Schlagwort(e): AERODYNAMICS
    Materialart: ; UG REVUE(
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  • 40
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    Design and performance evaluation of four transonic compressor rotors (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Transonic compressor rotors blade camberline shape optimization by various tip diffusion factor-ratio combinations
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; VUE SCIENTIFIQUE ET
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  • 41
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    Flow coefficients for supersonic nozzles with comparatively small radius of curvature throats (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Small curvature radius/throat radius ratio supersonic nozzles mass flow rate coefficients at high Reynolds numbers, appraising isentropic flow prediction methods
    Schlagwort(e): AERODYNAMICS
    Materialart: ; VUE SCIENTIFIQUE ET
    Format: text
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  • 42
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    Estimation of the maximum temperature of a swept leading edge for an equilibrium glide entry (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Maximum stagnation temperature on swept wing leading edge for equilibrium glide entry of space shuttle
    Schlagwort(e): AERODYNAMICS
    Materialart: ; 63 (
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  • 43
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    Detection of failure rate increases (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Systematic detection policies and Monte Carlo experiments on increased failure rate
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: The Deep Space Network, Vol. 4; p 95-100
    Format: text
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  • 44
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    Low frequency analysis of rocket engines using compressible propellants (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Low frequency analysis of rocket engines using compressible propellants
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA. MARSHALL SPACE FLIGHT CENTER PROC.- SPACE TRANSPORTATION SYSTEM PROPULSION TECHNOL. CONF., VOL. 1 28 APR. 1971; P 257-288
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  • 45
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    Bearings, lubricants, and seals for actuators and mechanisms (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Bearings, lubricants, and seals for lubricated and hydraulic components for space shuttle with high temperature and vacuum operating capabilities
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 2 APR. 1971; P 601-632
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  • 46
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    Problem, programming, and deck setup (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Computer programs for determining combustion stability of liquid propellant rocket engines
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: STABILITY CHARACTERIZATION OF ADVANCED INJECTORS, DESIGN GUIDE, VOL. 2 FEB. 1971 (SEE N71-20415 09-28)
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  • 47
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    Sharp slender cones in near-free-molecule hypersonic flow (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Shock tunnel drag measurements on sharp slender cones in near free molecule hypersonic flow in air and He
    Schlagwort(e): AERODYNAMICS
    Materialart: ; YAL SOCIETY (
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  • 48
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    Alleviation of vortex-induced heating to the lee side of slender wings in hypersonic flow (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Vortex-induced heating alleviation to lee side of slender wings in hypersonic flow by contouring leading edge planform
    Schlagwort(e): AERODYNAMICS
    Materialart: ; YAL SOCIETY (
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  • 49
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    The forge phase of friction welding. I, II (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Forge phase rigid and plastic region model of friction welding, deriving interfacial dispersion parameter of weld quality optimization
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: ; 9-12, 15 (
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  • 50
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    Auxiliary power unit - Introduction (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Program for developing hydrogen-oxygen fueled auxiliary power unit for space shuttle vehicle
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: PROC.- SPACE TRANSPORTATION SYSTEM PROPULSION TECHNOL. CONF., VOL. 3 28 APR. 1971; P 1097-1098
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  • 51
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    Correlation of space shuttle applicable experimental hypersonic aerodynamic characteristics with theory (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Hypersonic theoretical/experimental correlations of aerodynamic characteristics for space shuttle design
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 455-492
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  • 52
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    Consideration of Reynolds number simulation for subsonic shuttle tests (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Reynolds number simulation requirements for subsonic wind tunnel tests of space shuttle configurations
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA, WASHINGTON NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 423-453
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  • 53
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    Experimental load capacity and power loss of herringbone grooved gas lubricated journal bearings (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2011-08-16
    Beschreibung: Herringbone grooved gas lubricated journal bearing load capacity, attitude angle and power loss measurements
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: ; TA FREQUENZA (
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  • 54
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    Review of SERT II power conditioning (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: SERT 2 power conditioning, describing operating requirements, components construction, overload protection, system performance, etc
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; 6-8, 10-16 (
    Format: text
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  • 55
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    Static and dynamic aerodynamics of space shuttle vehicles (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Aerodynamic characteristics of delta wing space shuttle configurations
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 311-373
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  • 56
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    Approximate analytic solution for the position and strength of shock waves about cones in supersonic flow (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Approximate solution for position and strength of shock waves about cones in steady supersonic flow
    Schlagwort(e): AERODYNAMICS
    Materialart: ; ADEMIE DES SCIENCES
    Format: text
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  • 57
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    The NASA Quiet Engine Programme. (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Discussion of the experimental Quiet Engine developed under the NASA program to reduce jet aircraft noise levels. The current status of the program is given as follows: Aerodynamic evaluation of the three fans is complete and their acoustic evaluation is partially complete. Tests of fan casing boundary-layer section and of serrated leading edges on the half-scale B fan are complete and are underway on the half-scale C fan. Tests of the first engine with the A fan began in August 1971.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: Interavia; 26; Dec. 197
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  • 58
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    Airbreathing propulsion system trends. (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Among trends in airbreathing propulsion, the priority is shown to belong to the goal of quieting engines to a level no greater than the natural background noise level of the environment in which they operate. For military engines, not so severely noise-constrained, the possibility of stoichiometric gas-turbine engines is shown to be within reach. Very high bypass ratio propfans are especially suitable for V/STOL aircraft. Evolution of reliable variable-geometry inlets and exhaust nozzles characterizes trends in the supersonic regime.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: Astronautics and Aeronautics; 9; Nov. 197
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  • 59
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    Hypersonic boundary-layer transition in the presence of wind-tunnel noise. (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Description of additional results indicating that a unique relationship exists between rms sound pressure level and transition Reynolds number, provided all other parameters are held nearly invariant. The results illustrate the different levels of the transition Reynolds numbers obtained in six facilities with nearly invariant laminar boundary layers on the different models (at the same local unit Reynolds number) and indicate that some facility characteristic has a strong influence on the transition Reynolds numbers.
    Schlagwort(e): AERODYNAMICS
    Materialart: AIAA Journal; 9; Dec. 197
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  • 60
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    Acoustic Analysis of Solid Rocket Motor Cavities by a Finite Element Method (1971)
    In:  CASI
    Details
    Publikationsdatum: 2014-09-03
    Beschreibung: Adaptation of NASTRAN program to solve acoustic mode problems of solid rocket motor cavities by finite element method
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA. Langley Res. Center NASTRAN: Users Experiences; p 285-324
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  • 61
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    Analytical studies of contact of nominally flat surfaces - Effect of previous loading (1971)
    In:  Other Sources
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    Publikationsdatum: 2011-08-16
    Beschreibung: Previous plastic loading deformation effect on contact area, print number, size distribution and thermal conductivity for flat surfaces
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: ; - PHYSICAL AND RADIO
    Format: text
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  • 62
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    Reliability estimation procedures and CARE: The Computer-Aided Reliability Estimation Program (1971)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Ultrareliable fault-tolerant onboard digital systems for spacecraft intended for long mission life exploration of the outer planets are under development. The design of systems involving self-repair and fault-tolerance leads to the companion problem of quantifying and evaluating the survival probability of the system for the mission under consideration and the constraints imposed upon the system. Methods have been developed to (1) model self-repair and fault-tolerant organizations; (2) compute survival probability, mean life, and many other reliability predictive functions with respect to various systems and mission parameters; (3) perform sensitivity analysis of the system with respect to mission parameters; and (4) quantitatively compare competitive fault-tolerant systems. Various measures of comparison are offered. To automate the procedures of reliability mathematical modeling and evaluation, the CARE (computer-aided reliability estimation) program was developed. CARE is an interactive program residing on the UNIVAC 1108 system, which makes the above calculations and facilitates report preparation by providing output in tabular form, graphical 2-dimensional plots, and 3-dimensional projections. The reliability estimation of fault-tolerant organization by means of the CARE program is described.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: JPL Quart. Tech. Rev., Vol. 1, No. 3; p 17-26
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  • 63
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    Proceedings - Space Transportation System Propulsion Technology Conference. Volume 2 - Auxiliary propulsion system (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-01-29
    Beschreibung: Conference on auxiliary propulsion system performance and configurations for space shuttle applications - Vol. 2
    Schlagwort(e): PROPULSION SYSTEMS
    Format: application/pdf
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  • 64
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    Proceedings - Space Transportation System Propulsion Technology Conference. Volume 3 - Auxiliary power unit and air breathing propulsion (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-01-29
    Beschreibung: Design and development of auxiliary power unit and air breathing propulsion system for space shuttle vehicle
    Schlagwort(e): PROPULSION SYSTEMS
    Format: application/pdf
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  • 65
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    Long-duration firings of a Mariner Mars 1969 catalytic reactor (1971)
    In:  CASI
    Details
    Publikationsdatum: 2016-06-07
    Beschreibung: Two long-duration tests were conducted with a surplus Mariner Mars 1969 monopropellant hydrazine reactor in an attempt to induce the washout phenomenon. The Mariner Mars 1969 reactor was chosen because it has a long development history and thus is well characterized. No washout occurred during either of the two 1000-s tests, although slow transients were observed in the reactor operation during what were nominally steady-state conditions. The 2000-s of operating time represents nearly an order of magnitude increase over the rated life of the engine.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: JPL Quart. Tech. Rev., Vol. 1, No. 3; p 57-66
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  • 66
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    TOPS attitude propulsion subsystem technology (1971)
    In:  CASI
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    Publikationsdatum: 2016-06-07
    Beschreibung: The thermoelectric outer-planet spacecraft (TOPS) attitude propulsion subsystem effort is summarized. It includes the tradeoff rationale that went into the selection of anhydrous hydrazine as the propellant, and a brief description of three types of 0.445-N (100-mlbf) thrusters that were purchased for in-house evaluation. A discussion is also included of the 0.2224-N (50-mlbf)-developed thrusters and their integration with a portable, completely enclosed, propulsion module that was designed and developed to support the TOPS single-axis attitude control tests in the celestarium.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: JPL Quart. Tech. Rev., Vol. 1, No. 3; p 48-56
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  • 67
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    Acoustic testing of a 1.5 pressure ratio low tip speed fan with casing tip bleed (QEP Fan B scale model) (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A scale model of the bypass flow region of a 1.5 pressure ratio, single stage, low tip speed fan was tested with a rotor tip casing bleed slot to determine its effects on noise generation. The bleed slot was located 1/2 inch (1.3 cm) upstream of the rotor leading edge and was configured to be a continuous opening around the circumference. The bleed manifold system was operated over a range of bleed rates corresponding to as much as 6% of the fan flow at approach thrust and 4.25% of the fan flow at takeoff thrust. Acoustic results indicate that a bleed rate of 4% of the fan flow reduces the fan maximum approach 200 foot (61.0 m) sideline PNL 0.5 PNdB and the corresponding takeoff thrust noise 1.1 PNdB below the level with zero bleed. However, comparison of the standard casing (no bleed slot) and the slotted bleed casing with zero bleed shows that the bleed slot itself caused a noise increase.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-120822
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  • 68
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    Qualitative responses of a vortex core to tip blowing and intersecting airfoils (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The qualitative responses of a trailing vortex core to change in its convective velocity produced by injection of air into the vortex core and by the flow field of a lifting surface in the path of the core are discussed. Flow pictures of the vortex core and vorticity measurements in the core show that an axial momentum injection of approximately 35% of the total wing drag alters the vortex structure and behavior quite drastically by effectively inducing a more rapid dispersion of the vorticity in the core. The data indicate that the phenomenon is governed by the rate of injection of the momentum rather than the mass flow rate. There also seems to be an optimum rate of injection beyond which increased injection does not bring about equally significant changes in the vortex core. Flow patterns of the region of interaction between the flow field of a lifting surface and the vortex core show two modes of vortex response; (1) the vortex core bends, following the streamline shape until it intercepts the wake of the wing where it is abruptly dispersed, or (2) the vortex core may be sliced into two similar vortices when the vortex hits the leading edge of the wing.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-126675 , ASRL-TR-153-4
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  • 69
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    Satellite auxiliary-propulsion selection techniques. Addendum: A survey of auxiliary electric propulsion systems (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A review of electric thrusters for satellite auxiliary propulsion was conducted at JPL during the past year. Comparisons of the various thrusters for attitude propulsion and east-west and north-south stationkeeping were made based upon performance, mass, power, and demonstrated life. Reliability and cost are also discussed. The method of electrical acceleration of propellant served to divide the thruster systems into two groups: electrostatic and electromagnetic. Ion and colloid thrusters fall within the electrostatically accelerated group while MPD and pulsed plasma thrusters comprise the electromagnetically accelerated group. The survey was confined to research in the United States with accent on flight and flight prototype systems.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-126544 , JPL-TR-32-1505-ADD
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  • 70
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    Development of low cost fabrication techniques for large solid rocket nozzles (1971)
    In:  CASI
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    Publikationsdatum: 2019-06-27
    Beschreibung: Property measurements and fabrication characteristics were determined and the performance in subscale (Minuteman Wing 2 second stage) motors was evaluated. It was demonstrated that the incorporation of low cost fabrication techniques in a full scale 260 in. nozzle could result in savings of $149,000 when compared with an identical design using tape-wrapped components throughout.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-120900
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  • 71
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    Apollo 14 composite casting demonstration (1971)
    In:  CASI
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    Publikationsdatum: 2019-06-27
    Beschreibung: The purpose of the demonstration was to show that mixtures of materials of different specific gravities would remain stable in the liquid state and during freezing in low g and not segregate as they do on earth. An inflight demonstration was performed on the Apollo 14 mission during the translunar and and transearth coast periods. The apparatus consisted of an electrical heater, a heat sink device for cooling, and sealed metal capsules containing matrix materials having a low-melting point and dispersants. The evaluation of the demonstration samples was accomplished by comparing space processed (flight) samples with (control) samples processed on the ground under otherwise similar conditions. In the low q environment of space flight the dispersions of particles, fibers, and gases in a liquid metal matrix were maintained during solidification. Dispersions of normally immiscible liquids were also maintained during solidification.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA-TM-X-64641
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  • 72
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    Development of nondestructive testing techniques for plated-through holes in multilayer printed circuit boards (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The development of a nondestructive test with the capability to interrogate plated-through holes as small as 0.51 millimeters inside diameter is discussed. The system can detect defects such as holes, voids, cracks, and thin spots that reduce the current carrying capability of plates-through interconnects by 20 percent or more. Efforts were directed toward the design and fabrication of magnetic circuitry mutual coupling probes and to evaluate the effectiveness of these devices for detecting in multilayer board plated-through holes.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA-CR-61378 , C71-995/201
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  • 73
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    Analysis of transonic airfoils. (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: A finite difference scheme for the analysis of transonic airfoils at off-design conditions is described. It is the ultimate goal of the investigations to avoid expensive wind tunnel tests by combining the mathematical techniques in a procedure for designing supercritical airfoils so that they will be effective over a wider range of angles of attack and Mach numbers. A mathematical method is considered for computing two-dimensional transonic flows past a prescribed profile. The method can provide accurate results for a comparison with a known shockless regime. The approach gives also data of engineering reliability concerning the location and the strength of shocks at off-design conditions.
    Schlagwort(e): AERODYNAMICS
    Materialart: Communications on Pure and Applied Mathematics; 24; Nov. 197
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  • 74
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    Jet-noise reduction through liquid-base foam injection. (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: An experimental investigation has been made of the sound-absorbing properties of liquid-base foams and of their ability to reduce jet noise. Protein, detergent, and polymer foaming agents were used in water solutions. A method of foam generation was developed to permit systematic variation of the foam density. The investigation included measurements of sound-absorption coefficents for both plane normal incidence waves and diffuse sound fields. The intrinsic acoustic properties of foam, e.g., the characteristic impedance and the propagation constant, were also determined. The sound emitted by a 1-in.-diam cold nitrogen jet was measured for subsonic (300 m/sec) and supersonic (422 m/sec) jets, with and without foam injection. Noise reductions up to 10 PNdB were measured.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: Acoustical Society of America; vol. 50
    Format: text
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  • 75
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    Numerical solution of flowfields behind rectangular wings (1971)
    In:  CASI
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    Publikationsdatum: 2019-06-27
    Beschreibung: The numerical solution of flow fields behind rectangular wings is described. Subjects discussed are: (1) evaluation of various differencing methods applied to the hyperbolic partial differential equations encountered in gas dynamics, (2) application of the numerical differencing techniques to the wedge flow, two dimensional shock reflection for the three dimensional finite thickness wing at zero degrees angle of attack, and (3) calculation of preliminary results for wedge flows using optimum differencing methods.
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-CR-126214 , ISU-ERI-AMES-71015
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  • 76
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    Demonstration of a sterilizable solid rocket motor system, addendum (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Technical emphasis was placed on characterization of a scaled-up batch of the improved propellant formulation and determination of the effects of dry heat sterilization on propellant integrity and structural response. The grain stress analysis was directed toward tailoring a fully-bonded grain to the calculated propellant allowable stresses and investigating various bond release concepts to relieve stresses incurred in thermal shrinkage following sterilization.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-111889
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  • 77
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    LF460 detail design (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: This is the final technical report documenting the detail design of the LF460, and advanced turbotip lift fan intended for application with the YJ97-GE-100 turbojet jet generator to a V/STOL transport research aircraft. Primary objective of the design was to achieve a low noise level while maintaining the high thrust/weight ratio capability of a high pressure ratio lift fan. Report covers design requirements and summarizes activities and final results in the areas of aerodynamic and mechanical design, component and system performance, acoustic features and final noise predictions.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-120787 , DOC-71-AEG-297
    Format: application/pdf
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  • 78
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    Reliability model of a monopropellant auxiliary propulsion system (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A mathematical model and associated computer code has been developed which computes the reliability of a monopropellant blowdown hydrazine spacecraft auxiliary propulsion system as a function of time. The propulsion system is used to adjust or modify the spacecraft orbit over an extended period of time. The multiple orbit corrections are the multiple objectives which the auxiliary propulsion system is designed to achieve. Thus the reliability model computes the probability of successfully accomplishing each of the desired orbit corrections. To accomplish this, the reliability model interfaces with a computer code that models the performance of a blowdown (unregulated) monopropellant auxiliary propulsion system. The computer code acts as a performance model and as such gives an accurate time history of the system operating parameters. The basic timing and status information is passed on to and utilized by the reliability model which establishes the probability of successfully accomplishing the orbit corrections.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-131400 , AMS-997
    Format: application/pdf
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  • 79
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    A note on multiple pure tone noise. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A theoretical investigation of multiple pure tone noise is presented. An analysis based on a two-dimensional inviscid flow model is developed to predict the generation and subsequent evolution of multiple pure tone noise from prescribed blade-to-blade nonuniformities in the rotor geometry. The results show that even small nonuniformities within manufacturing tolerances can be a significant source of multiple pure tone noise. Among the nonuniformities investigated, errors in blade spacing are less significant multiple pure tone noise sources than errors in blade stagger or blade contours.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: Journal of Sound and Vibration; 19; Dec. 22
    Format: text
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  • 80
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    A generalized theory on the noise generation from supersonic shear layers. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A generalization is presented of Phillips' (1960) theory of noise generation by supersonic turbulent shear layers. Both Mach wave radiation and non-Mach wave noise radiation mechanisms are considered. The range of validity of Phillips' theory has been expanded to include the low supersonic and transonic ranges. These generalizations are important not only for their analytical rigor, but also for their prospective applications to practical problems in jet noise prediction and control. The noise generation mechanisms in a supersonic jet are found to differ from those in a subsonic jet. The theory is considered to offer some prospects of answering important questions in supersonic jet noise, such as noise source distribution, mean flow refraction effects, directivity, spectrum, and efficiency of noise radiation.
    Schlagwort(e): AERODYNAMICS
    Format: text
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  • 81
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    Autorotating wings - An experimental investigation. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The autorotation of a flat plate about its spanwise axis was experimentally studied. Most of the work was done with a wing mounted in a 5 x 7 ft low-speed wind tunnel. The measurements consisted of the unsteady lift, drag, angular acceleration and the wing rotation rate. The flow pattern was very different from that over a static wing. The maximum and average lift, drag and angular acceleration were measured for Reynolds numbers from 25,000 to 250,000. The effect of applying driving and retarding torques to the wing was studied. A variety of wing configurations were tested, together with freely falling wings. For Reynolds numbers above 4000 the average lift and drag coefficients were comparable to those observed in the fixed axis tests, and it appeared that the flow pattern was similar.
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of Fluid Mechanics; 50; Dec. 14
    Format: text
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  • 82
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    Performance of continuum gas viscoseals. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Viscoseals performance as predicted by three different analytical models is compared with experimental data for air as the continuum gas sealant. An experimental investigation has been conducted on two multiple-grooved two-inch diameter viscoseals up to shaft speeds of 35,000 rpm. The two seal geometries considered differ significantly insofar as groove aspect ratio is concerned. The results of this continuum investigation of sealing coefficient for the gas viscoseals suggest that the Boon and Tal model is a good design tool for the laminar continuum regime provided it is restricted to high aspect ratio groove applications.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Format: text
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  • 83
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    Hypersonic bodies of maximum drag for a given lift-to-drag ratio. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The problem considered in this paper is concerned with the aerodynamic design of the forebody shape of reentry vehicles in the blunt, homothetic, elliptic transversal contour, power-law longitudinal contour, raked-off configurational set. In particular, the forebody shape which maximizes the ratio of the forebody pressure drag to the free-stream dynamic pressure for a given lift-to-drag ratio and given geometric properties is determined. This problem is considered because recent survey articles indicate that its solution will provide useful qualitative design information about manned vehicles entering the earth's atmosphere from any of the foreseeable planetary missions. Single-integral equations relating the lift and drag in Newtonian hypersonic flow to the forebody geometry are derived and used to formulate the optimization problem which is solved by a direct numerical method.
    Schlagwort(e): AERODYNAMICS
    Materialart: Journal of the Astronautical Sciences; 19; Sept
    Format: text
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  • 84
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    Experimental load capacity and power loss of herringbone grooved gas lubricated journal bearings. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Load capacity, attitude angle, and power loss were determined for 1-1/2-in.-diam herringbone grooved journal bearings operating in air to speeds of 60,000 rpm. Results showed that groove-to-ridge-clearance ratios of 2.0 to 2.4 give a greater load capacity than do ratios outside this optimum range. Agreement with a small-eccentricity pressure perturbation theory was good for groove-to-ridge-clearance ratios in the optimum range. Power loss, relative to that calculated for a plain bearing of the same dimensions, did not vary widely for the range of geometric variables used. Relative power loss generally increased with speed and was generally comparable to that for a plain bearing.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: ASME PAPER 71-LUB-B
    Format: text
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  • 85
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    Rocket propulsion by thermonuclear micro-bombs ignited with intense relativistic electron beams. (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Discussion of a method for the ignition of a thermonuclear microbomb by means of an intense relativistic electron beam with regard to its potential application to rocket propulsion. With such a system, exhaust velocities up to 1000 km/sec, corresponding to a specific impulse of 100,000 sec, seem to be within the realm of possibility. The rocket is propelled by a chain of thermonuclear microbombs exploded in a concave magnetic mirror produced by superconducting field coils. The magnetic pressure of the field reflects the fireball generated by the explosion. For the large capacitor bank required to generate the intense relativistic electron beam, a desirable lightweight design may be possible through use of ferroelectric materials. Because of the high cost of the T-D and He 3-D thermonuclear material, the system has to be optimized by minimizing the T-D and He 3-D consumption by a proper TD and He 3-D fuel to hydrogen propellant mass ratio, leading to a larger total system mass than would be absolutely necessary.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: AD-746766 , AFOSR-72-1355TR , Raumfahrtforschung; 15; Sept
    Format: text
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  • 86
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    Experimental quiet engine program aerodynamic performance of fan A (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The aerodynamic component test results are presented of fan A, one of two high-bypass-ratio, 1160 feet per second single-stage fans, which was designed and tested as part of the NASA Experimental Quiet Engine Program. This fan was designed to deliver a bypass pressure ratio of 1.50 with an adiabatic efficiency of 86.5% at a total fan flow of 950 lb/sec. It was tested with and without inlet flow distortion. A bypass total-pressure ratio of 1.52 and an adiabatic efficiency of 88.3% at a total fan flow of 962 lb/sec were actually achieved. An operating margin of 12.4% was demonstrated at design speed.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-120858
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  • 87
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    Mass, momentum and energy flow from an MPD accelerator (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The mass, momentum, and energy flows are measured over a current range of 8 to 50 kA and inlet mass flows of 2 to 36q/sec of argon. The momentum flux profile indicates that the accelerator produces a uniform, 2-inch diameter axial jet at the anode which expands into a Gaussian profile at an axial station 11 inches from the anode. The electromagnetic component of the thrust is found to follow the familiar quadratic dependence on arc current, while a more complex empirical relation is needed to correlate the gasdynamic contribution with the current and mass flow rate. Using available time-of-flight velocity profiles at a current of 16 kA and a mass flow of 5.9 g/sec, calculated flux profiles of mass and kinetic energy exhibit a tendency for some fraction of the inlet mass flow to leak out at a low velocity around the central high velocity core.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-127120 , REPT-999
    Format: application/pdf
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  • 88
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    A survey of Kaufman thruster cathodes (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A survey is presented of the various cathodes which were developed and used in the Kaufman ion thruster. The electron bombardment type ion source is briefly described. The general design, operating characteristics, and power requirements are shown for each type of cathode from the refractory metals used in 1960 to the plasma discharge hollow cathodes of today. A detailed discussion of the hollow cathode is given, including starting and cyclic operating characteristics as well as more fundamental design parameters. Tests to date show that the plasma hollow cathode is an efficient electron source with demonstrated durability over 10,000 hours.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-68386 , BNL Proc. of the Symp. on Ion Sources and Formation of Ion Beams; p 93-101
    Format: text
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  • 89
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    Ion sources for electric propulsion (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Ion systems, which accelerate ions of Cs, Hg, or colloid particles by electrostatic fields, are furthest advanced and ready for application. Four kinds of ion sources have been developed: The contact ionization source for Cs as propellants, the electron bombardment source for Cs or Hg, the RF ionization source for Hg, and the hollow needle spray nozzle for colloidal glycerol particles. In each case, the ion beam must be neutralized by injection of electrons shortly behind the exit orifice to avoid adverse space charge effects.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-68383 , BNL Proc. of the Symp. on Ion Sources and Formation of Ion Beams; p 47-60
    Format: text
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  • 90
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    Modified RS2101 rocket engine study program (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The purpose of the program is to perform design studies and analyses to determine the effects of incorporating a 60:1 expansion area ratio nozzle extension, extended firing time, and modified operating conditions and environments on the MM'71 rocket engine assembly. An injector-to-thrust chamber seal study was conducted to define potential solutions for leakage past this joint. The results and recommendations evolving from the engine thermal analyses, the injector-to-thrust chamber seal studies, and the nozzle extension joint stress analyses are presented.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-127386 , SER-1159/RS21/1001
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  • 91
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    Kaufman thruster development at Lewis Research Center (LeRC) (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: The current status of research programs on mercury electron bombardment thrusters is reviewed. Future thruster requirements predicted from mission analysis are briefly discussed to establish the relationship with present programs. Thrusters ranging in size from 5 to 150 cm diameter are described. These thrusters have possible near to far term applications extending from stationkeeping to primary propulsion. Beam currents range from 10 mA at to 25 A at accelerating potentials of 500 to 5000 V.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-68385 , BNL Proc. of the Symp. on Ion Sources and Formation of Ion Beams; p 85-92
    Format: text
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  • 92
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    Viscoseal performance with rarefied-gas sealant (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A fundamental study of viscoseals having a rarefied gas as the sealant has been conducted. Both experimental and analytical investigations are reported. Three different analytical models have been formulated and are described in detail. An experimental investigation has been conducted on multiple grooved two-inch diameter viscoseals over a wide range of gas densities and shaft speeds up to 30,000 rpm. Comparisons are presented between actual viscoseal performance and the theoretical predictions for both sealing coefficient and net leakage parameters as functions of the degree of gas rarefication. Recommendations are presented for the use of the analytical models.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA-CR-120911 , AE-71-023-9
    Format: application/pdf
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  • 93
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    Friction, wear, and lubrication in vacuum (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A review of studies and observations on the friction, wear, and lubrication behavior of materials in a vacuum environment is presented. The factors that determine and influence friction and wear are discussed. They include topographical, physical, mechanical, and the chemical nature of the surface. The effects of bulk properties such as deformation characteristics, fracture behavior, and structure are included.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA-SP-277 , LC-72-174581
    Format: application/pdf
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  • 94
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    Fabrication of titanium thermal protection system panels by the NOR-Ti-bond process (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A method for fabricating titanium thermal protection system panels is described. The method has the potential for producing wide faying surface bonds to minimize temperature gradients and thermal stresses resulting during service at elevated temperatures. Results of nondestructive tests of the panels are presented. Concepts for improving the panel quality and for improved economy in production are discussed.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA-CR-123536 , NOR-71-202
    Format: application/pdf
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  • 95
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    A system reliability analysis for stand-by spares with non-zero unpowered failure rates (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Equations which define the reliability of n-fold parallel systems with stand-by spares, and triply redundant, majority-voting systems with stand-by spares have been derived. The stand-by spares have been assumed to have a non-zero failure rate while in the stand-by mode. A Monte Carlo system simulation has been generated and the results compared to the theoretical reliability predictions. A comparison of these two stand-by configurations is also presented for three through six total units.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA-CR-61372
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  • 96
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    Improved scaling laws for stage inert mass space Propulsion systems. Volume 3: Propulsion synthesis program users and programmers manual (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The analytical models developed for the Space Propulsion Automated Synthesis Modeling (SPASM) program are presented. Weight scaling laws developed during this study are incorporated into the program's scaling data bank. A detail listing, logic diagram and input/output formats are supplied for the SPASM program. Two test examples for one to four-stage vehicles performing different types of missions are shown to demonstrate the program's capability and versatility.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-114421 , SD-71-534-3-VOL-3
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  • 97
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    Improved scaling laws for stage inert mass of space propulsion systems. Volume 1: Summary (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Summarized is a study which satisfies the need for improved scaling laws for stage inert mass of space propulsion systems. The resulting laws are applicable to current and future vehicle systems and designs for a comprehensive spectrum of anticipated planetary missions.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-114419 , SD-71-534-1-VOL-1
    Format: application/pdf
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  • 98
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    Improved scaling laws for stage inert mass of space propulsion systems. Volume 2: System modeling and weight data (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Technical models and analytical approaches used to develop the weight data for vehicle system concepts using advanced technology are reported. Weight data are supplied for the following major system elements: engine, pressurization, propellant containers, structural shells and secondary structure, and environmental protection shields for the meteoroid and thermal design requirements. Scaling laws, improved and a simplified set, are developed from the system weight data. The laws consider the implications of the major design parameters and mission requirements on the stage inert mass.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-114420 , SD-71-534-2-VOL-2
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  • 99
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    Monopropellant hydrazine resisto jet (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Mathematical models for the electrothermal hydrazine thruster are provided which can be utilized to aid in preliminary design definition, interpretation of test data, and the evaluation of design and operational changes. Three computer programs were formulated to provide the necessary steady state and transient performance design tools. These included: preliminary evaluation of the energy balance characteristics of the thruster; a means of evaluating steady state performance relative to the primary design, configuration, and operational parameters; and a model to provide a means of evaluating transient (pulse mode) operation of the thruster relative to primary design and operational parameters.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-122347 , TRW-20266-6006-R0-00
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  • 100
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    Bipropellant shut-off valve (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: An advanced design of an all metal, fast response, bipropellant, shut-off valve for use on long duration space missions is reported. The valve provides the flow control capability for a 1,000 lb thrust, bipropellant engine using oxygen difluoride and diborane as propellants. The shutoff seal selection is a soft-on-hard metal concept. The soft seal is a spherical shell that seats against a hard conical seat. Beryllium copper and beryllium nickel seals were selected to seal against an electrolyzed Inconel 718 seat. Poppet shaft sealing is achieved by use of hydroformed, Inconel 718 bellows. Two valve assemblies were fabricated and subjected to a series of tests including leak, response time, flow capacity, dry cycles, water cycles, liquid nitrogen cycles, liquid fluorine cycles, and lead-lag operation cycles. These tests demonstrated the ability of the valve to meet design goals.
    Schlagwort(e): MACHINE ELEMENTS AND PROCESSES
    Materialart: NASA-CR-125611 , REPT-7-733-2F
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