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  • General Chemistry  (2.222)
  • PROPULSION SYSTEMS  (618)
  • Cell & Developmental Biology
  • 1980-1984
  • 1970-1974  (1.677)
  • 1965-1969  (1.536)
  • 1971  (1.677)
  • 1969  (1.536)
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  • 1980-1984
  • 1970-1974  (1.677)
  • 1965-1969  (1.536)
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  • 1
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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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  • 2
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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
    Format: text
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  • 3
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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
    Format: text
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  • 4
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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
    Format: text
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  • 5
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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
    Format: text
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  • 6
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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
    Format: text
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  • 7
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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
    Format: text
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  • 8
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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
    Format: text
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  • 9
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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
    Format: text
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  • 10
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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
    Format: text
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  • 11
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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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  • 12
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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
    Format: text
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  • 13
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    Electrical power systems for space - Achievements and issues (1971)
    In:  Other Sources
    Details
    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. (
    Format: text
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  • 14
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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
    Format: text
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  • 15
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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
    Format: text
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  • 16
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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)
    Format: text
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  • 17
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    Auxiliary power unit - Introduction (1971)
    In:  Other Sources
    Details
    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
    Format: text
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  • 18
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    Review of SERT II power conditioning (1971)
    In:  Other Sources
    Details
    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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  • 19
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    The NASA Quiet Engine Programme. (1971)
    In:  Other Sources
    Details
    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
    Format: text
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  • 20
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    Airbreathing propulsion system trends. (1971)
    In:  Other Sources
    Details
    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
    Format: text
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  • 21
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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
    Format: text
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  • 22
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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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  • 23
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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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  • 24
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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
    Format: application/pdf
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  • 25
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    TOPS attitude propulsion subsystem technology (1971)
    In:  CASI
    Details
    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
    Format: application/pdf
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  • 26
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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
    Format: application/pdf
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  • 27
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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
    Format: application/pdf
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  • 28
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    Development of low cost fabrication techniques for large solid rocket nozzles (1971)
    In:  CASI
    Details
    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
    Format: application/pdf
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  • 29
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    Jet-noise reduction through liquid-base foam injection. (1971)
    In:  Other Sources
    Details
    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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  • 30
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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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  • 31
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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
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  • 32
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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
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  • 33
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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
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  • 34
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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
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  • 35
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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
    Format: application/pdf
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  • 36
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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
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  • 37
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    A survey of Kaufman thruster cathodes (1971)
    In:  Other Sources
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    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
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  • 38
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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
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  • 39
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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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  • 40
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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
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  • 41
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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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  • 42
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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
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  • 43
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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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  • 44
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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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  • 45
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    Installation and integration of transonic transport propulsion systems. (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-07-27
    Beschreibung: Initial work indicates that a viable aircraft family can be designed for higher subsonic cruise speeds. Studies to date suggest that the propulsion system/nacelle design and the incorporation of noise attenuation into this design will have more influence on the choice of an optimum engine than engine weight and fuel consumption. These studies also suggest the payoff resulting from the incorporation of new technology items such as the internal engine generator and new structural cowl concepts because of the greater sensitivity to drag. These factors, plus the greater interdependency of the transonic aircraft and its propulsion system, point up the importance of a total system approach to propulsion system optimization and design.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: SAE PAPER 710762 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
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  • 46
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    Performance of a 10 mlb biowaste resistojet. (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-07-27
    Beschreibung: Description of the thrusting performance of a 10-mlb thrust, concentric-tubes biowaste resistojet, which was life tested on hydrogen and ammonia propellants for 8000 hours. Thrusting performance is presented for H2, H2O, CH4, and CO2 as well as typical biopropellant mixtures CO2-CH4, H2O-CH4 and CO2-H2O. Using Pt-Ir alloy heater tubes, 235 and 575 seconds were obtained for water and hydrogen propellants. Overall total power efficiencies were 66%, which includes losses for a preevaporator close-coupled for the water tests. Vibration to 1.0 sq q/Hz with an overall G rms of 36, shock at 30 g's and acceleration to 8 g's simulating a launch were passed by the thrustor.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: SAE PAPER 710769 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
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  • 47
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    The NASA Quiet Engine. (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-07-27
    Beschreibung: The NASA Quiet Engine Program will incorporate all available noise-reduction technology into a propulsion system suitable for subsonic civil transport aircraft. Full-scale experimental hardware is being built and tested primarily for noise performance. The program is in process, and component tests to date indicate that it is possible to achieve or exceed noise reduction objectives of 15-20 PNdB below the levels of 707/DC-8 long-range transport aircraft.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: SAE PAPER 710774 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
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  • 48
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    Development of the Algol III solid rocket motor for SCOUT. (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-07-27
    Beschreibung: The design and performance of a motor developed for the first stage of the NASA SCOUT-D and E launch vehicles are discussed. The motor delivers a 30% higher total impulse and a 35 to 45% higher payload mass capability than its predecessor, the Algol IIB. The motor is 45 in. in diameter, has a length-to-diameter ratio of 8:1 and delivers an average 100,000-lb thrust for an action time of 72 sec. The motor design features a very high volumetrically loaded internal-burning charge of 17% aluminized polybutadiene propellant, a plasma-welded and heat-treated steel alloy case, and an all-ablative plastic nose liner enclosed in a steel shell. The only significant development problem was the grain design tailoring to account for erosive burning effects which occurred in the high-subsonic-Mach-number port. The tests performed on the motor are described.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: SAE PAPER 710765 , Society of Automotive Engineers, National Aeronautic and Space Engineering and Manufacturing Meeting; Sept. 28-30, 1971; Los Angeles, CA
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  • 49
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    Application of hybrid propulsion systems to planetary missions (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The feasibility and application of hybrid rocket propulsion to outer-planet orbiter missions is assessed in this study and guidelines regarding future development are provided. A Jupiter Orbiter Mission was selected for evaluation because it is the earliest planetary mission which may require advanced chemical propulsion. Mission and spacecraft characteristics which affect the selection and design of propulsion subsystems are presented. Alternative propulsion subsystems, including space-storable bipropellant liquids, a solid/monopropellant vernier, and a hybrid, are compared on the basis of performance, reliability, and cost. Cost-effectiveness comparisons are made for a range of assumptions including variation in (1) the level of need for spacecraft performance (determined in part by launch vehicle injected mass capability), and (2) achievable reliability at corresponding costs. The results indicated that the hybrid and space-storable bipropellant mechanizations are competitive.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-123356 , JPL-TM-33-483
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  • 50
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    Integral lift engine preliminary design (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A preliminary mechanical design of a complete lift fan engine system is reported. A description of the lift fan engine, layout drawings of the components and complete engine, and a discussion of the design analyses and results are presented. The design features and areas of analysis include fan and compressor rotor blades of composite construction, a combustor folded over the compressor, relatively high-temperature blades in the high-pressure turbine, the first stage of the low-pressure turbine used for bearing support and ducting of lubricant to the bearings, a complete lubrication system, critical speeds of the shafting, and vibration and flutter of the blading.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-120838 , CW-WR-71-091F
    Format: application/pdf
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  • 51
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    Soot oxidation rates in gas turbine engines (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A basis is proposed for extrapolating soot oxidation rate measurements obtained in laboratory flames to the more extreme operating conditions of gas turbine combustion chambers. The proposal is based on the observation that, within probable experimental uncertainty, the limited soot oxidation measurements correlate with the more extensive measurements of the surface oxidation rates of macroscopic samples of pyrographite. The soot oxidation rates thus determined for the conditions of a typical gas turbine combustion chamber are considerably lower than estimates which were based on simple extrapolations of the flame data.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-125404 , FML-PUBL-71-12
    Format: application/pdf
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  • 52
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    A study of performance and cost improvement potential of the 120 inch (3.05 m) diameter solid rocket motor. Volume 2: Study approach and detailed results (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: For abstract, see N72-14799.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-114390 , UTC-2401-FR-VOL-2
    Format: application/pdf
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  • 53
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    Variable geometry aft-fan for takeoff quieting or thrust augmentation of a turbojet engine (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A concept is presented that combines the low-noise and high-thrust characteristics of a turbofan at takeoff, together with its high efficiency at subsonic flight speeds, with the high efficiency of a turbojet at supersonic cruise. It consists of a free turbine with tip fan mounted behind the turbine of a conventional turbojet engine. Fan air is supplied from blow-in doors or is ducted from the main engine inlet. At high flight speeds where fan augmentation is not desirable, the fan inlet is closed and the free turbine is stopped by adjustment of its variable-camber stators. Estimates of noise, cycle performance, and example configurations are presented for a typical supersonic transport application.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: E-6714 , NASA-TM-X-67983
    Format: application/pdf
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  • 54
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    Effect of two types of helium circulators on the performance of a subsonic nuclear powered airplane (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Two types of helium circulators are analytically compared on the bases of their influence on airplane payload and on propulsion system variables. One type of circulator is driven by the turbofan engines with power takeoff shafting while the other, a turbocirculator, is powered by a turbine placed in the helium loop between the nuclear reactor and the helium-to-air heat exchangers inside the engines. Typical results show that the turbocirculator yields more payload for circulator efficiencies greater than 0.82. Optimum engine and heat exchanger temperatures and pressures are significantly lower in the turbocirculator case compared to the engine-driven circulator scheme.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2237 , E-5811
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  • 55
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    Sphere drag in solid rockets - Non-continuum and turbulence effects (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: Momentum transfer between gas and condensed phase in metallized solid propellant rocket motors, measuring noncontinuum and turbulence effects on sphere drag
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; TROPHYSICAL JOURNAL
    Format: text
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  • 56
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    Design and development of a small structurally integrated ion thruster system (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: A 5 cm structurally integrated ion thruster has been developed for attitude control and stationkeeping of synchronous satellites. With 2-D vectorable grids, thrust is 0.56 mlb at a beam voltage of 1200 V, total mass efficiency is 64%, and electrical efficiency is 46.8%. Nonvectoring thrust of 0.41 is demonstrated at very low specific impulse with dielectric coated grids. Structural integrity is demonstrated with dielectric coated grids for shock (30 G), sinusoidal (9 G), and random (19 G squared/Hz) accelerations. System envelope is 31.6 cm long by 14 cm flange B.C. with a mass of 8.5 kg including 6.2 Kg mercury propellant.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-120821
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  • 57
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    Solar electric propulsion system technology (1971)
    In:  CASI
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    Publikationsdatum: 2019-06-27
    Beschreibung: Achievements in the solar electric propulsion system technology program (SEPST 3) are reported and certain propulsion system-spacecraft interaction problems are discussed. The basic solar electric propulsion system concept and elements are reviewed. Hardware is discussed only briefly, relying on detailed fabrication or assembly descriptions reported elsewhere. Emphasis is placed on recent performance data, which are presented to show the relationship between spacecraft requirements and present technology.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-124572 , JPL-TM-33-510
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  • 58
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    Boron epoxy rocket motor case program (1971)
    In:  CASI
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    Publikationsdatum: 2019-06-27
    Beschreibung: Three 28-inch-diameter solid rocket motor cases were fabricated using 1/8 inch wide boron/epoxy tape. The cases had unequal end closures (4-1/8-inch-diameter forward flanges and 13-inch-diameter aft flanges) and metal attachment skirts. The flanges and skirts were titanium 6Al-4V alloy. The original design for the first case was patterned after the requirements of the Applications Technology Satellite apogee kick motor. The second and third cases were designed and fabricated to approximate the requirements of a small Applications Technology Satellite apogee kick motor. The program demonstrated the feasibility of designing and fabricating large-scale filament-wound solid propellant rocket motor cases with boron/epoxy tape.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-125445 , MCR-71-223
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  • 59
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    Flight investigation of airframe installation effects on an auxiliary inlet ejector nozzle on an underwing engine nacelle (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The local flow field approaching an installed nozzle may vary from isolated test conditions, thereby affecting exhausting nozzle performance. An installation of general interest is a podded engine mounted near the aft lower surface of the wing. The effect of this installation on the performance of an auxiliary inlet ejector nozzle was investigated over a Mach number range of 0.7 to 1.3 by using a modified F-106B aircraft. Both floating and fixed-open door configurations were examined. The ejector nozzle trailing-edge flaps were simulated in the closed position with rigid structure which provided a boattail angle of 15 deg. Primary nozzle area was varied as exhaust gas temperature was varied between 982.2 and 2003.3 K.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2396 , E-6208
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  • 60
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    A description of the thruster attitude control simulation and its application to the HEAO-C study (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: During the design and evaluation of a reaction control system (RCS), it is desirable to have a digital computer program simulating vehicle dynamics, disturbance torques, control torques, and RCS logic. The thruster attitude control simulation (TACS) is just such a computer program. The TACS is a relatively sophisticated digital computer program that includes all the major parameters involved in the attitude control of a vehicle using an RCS for control. It includes the effects of gravity gradient torques and HEAO-C aerodynamic torques so that realistic runs can be made in the areas of fuel consumption and engine actuation rates. Also, the program is general enough that any engine configuration and logic scheme can be implemented in a reasonable amount of time. The results of the application of the TACS in the HEAO-C study are included.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-64660
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  • 61
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    Maximum propellant utilization in an electron bombardment thruster (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: Current theory and experimental data on propellant utilization in electron bombardment ion thrusters are reviewed. Because the majority of investigations have been conducted with mercury, the presentation emphasizes that propellant. The results are presented in as general a form as possible to facilitate use in areas other than space propulsion.
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-68384 , BNL Proc. of the Symp. on Ion Sources and Formation of Ion Beams; p 61-68
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  • 62
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    A single mode approximation in the solution of nonlinear combustion instability problems (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: Nonlinear combustion stability problems in liquid propellant rocket engines, describing unsteady combustion response by Crocco time lag hypothesis
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; UGREVUE(
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  • 63
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    Electrohydrodynamics of a current-carrying semi-insulating jet (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: Quasi-one dimensional nonlinear model of electrohydrodynamic stability and control of current carrying semiinsulating jets at supercritical and subcritical regimes
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; OMBUSTION IN A FLOW
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  • 64
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    Directional acoustic radiation from a supersonic jet generated by shear layer instability (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: Directional acoustic radiation from supersonic jet, discussing generation mechanism theory based on shear layer instability close to nozzle
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; TA FREQUENZA (
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  • 65
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    Injector design criteria using noncircular orifice geometry (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: Rocket engine propellant injectors with noncircular orifice geometry, presenting experimental spray patterns and predicted performance for noncircular and circular orifice configurations
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; IENCES (
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  • 66
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    Thrust from arcjets with self-induced magnetic fields (1971)
    In:  Other Sources
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    Publikationsdatum: 2019-06-27
    Beschreibung: Closed form formula for plasma thrust from arc jets with self induced magnetic fields, predicting electrode erosion and entrainment
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: ; IENCES (
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  • 67
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    NASA turbine cooling research status report, 1971 (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Flow and heat transfer technology resulting from NASA turbine cooling program
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2384 , E-6164
    Format: application/pdf
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  • 68
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    High pressure performance of combustor segments utilizing pressure-atomizing fuel nozzles and air swirlers for primary-zone mixing (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Primary and secondary mixing performance of combustors under high inlet air pressures
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TN-D-6491 , E-6156
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 69
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    Beam focusing characteristics of variously shaped grid holes (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Beam focusing characteristics of variously shaped grid holes with application to electron bombardment ion thrustors
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67922
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 70
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    Quasi-steady and short pulse discharge thruster experiments (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Propulsive performance and erosion behavior of accelerator nozzle operating as short pulse discharge or quasi-steady solid Teflon propellant plasma thruster
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-111935 , PCD-TR-71-3 , FHR-3795-1
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 71
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    Tip-turbine lift package design (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Tip-turbine lift fan design and specifications
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-72974 , CW-WR-71-034.F
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 72
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    Effect of stator-rotor axial clearance on cold-air performance of a turbine with transpiration-cooled stator blading (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Stator-rotor axial clearance effects on cold air performance of turbine with sweat cooled stator blades
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67914
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 73
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    Kaufman thruster development at Lewis Research Center (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Optimization of mercury electron bombardment thrusters in SERT program
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67915 , E-6539
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 74
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    Composite accelerator grid investigation for cesium electron bombardment ion thruster Final report, 28 May 1969 - 28 Apr. 1971 (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Fabrication and testing of bonded metal-ceramic, glass-coated metal, and glass-coated ceramic bonded to metal composite electrodes for cesium bombardment ion thrusters
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-119695
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 75
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    Effect of operating variables on pollutant emissions from aircraft turbine engine combustors (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Operational methods for control of air pollution emissions from aircraft turbine engine combustor
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67887
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 76
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    Comparative performance of nuclear and cryogenic chemical space propulsion systems (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Comparative performance of solid core nuclear and cryogenic chemical space propulsion systems
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2352
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 77
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    The NASA quiet engine (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Application of noise reduction technology to design of propulsion system for subsonic civil transport aircraft
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67884
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 78
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    Captive-fired Testing of Solid Rocket Motors - Space Vehicle Design Criteria /chemical Propulsion/ (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Captive-fired testing of solid rocket motors for design criteria
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-SP-8041
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 79
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    Development and testing of ablative rocket engine with selected 7.62-centimeter /3.0 in/ diameter throat inserts (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Development and testing of ablative rocket engine with selected 7.62 cm /3.0 in./ diameter throat inserts, and testing of zirconia reinforced with tungsten-rhenium wire for throat insert material
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2315 , E-6197
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 80
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    Space shuttle propulsion systems on-board checkout and monitoring system development study. Volume 1 - Summary Final report (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Development of onboard checkout equipment and performance monitoring capability for space shuttles - Vol. 1
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-119837 , MCR-71-62-VOL-1
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 81
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    Booster and orbiter engine studies (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Air breathing, hydrogen fueled engine studies for space shuttle application
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA. MARSHALL SPACE FLIGHT CENTER PROC.- SPACE TRANSPORTATION SYSTEM PROPULSION TECHNOL. CONF., VOL. 3 28 APR. 1971; P 1225-1255
    Format: text
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  • 82
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    Optimal control of supersonic inlets to minimize unstarts (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Design and characteristics of supersonic inlet controls for minimizing inlet unstarts
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TN-D-6408 , E-6253
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 83
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    Combustion oscillations damping devices (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Damping devices for controlling combustion oscillations in rocket thrust chambers
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA. MARSHALL SPACE FLIGHT CENTER PROC.- SPACE TRANSPORTATION SYSTEM PROPULSION TECHNOL. CONF., VOL. 1 28 APR. 1971; P 173-197
    Format: text
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  • 84
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    Final results of the XLR129 program (1971)
    In:  Other Sources
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Design, engineering mockup, and performance tests on XLR129 reusable rocket engine
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA. MARSHALL SPACE FLIGHT CENTER PROC.- SPACE TRANSPORTATION SYSTEM PROPULSION TECHNOL. CONF., VOL. 1 28 APR. 1971; P 31-73
    Format: text
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  • 85
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    Space shuttle propulsion systems on-board checkout and monitoring system development study. Volume 2 - Propulsion system definition and criteria Final report (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Description of design reference model for space shuttle propulsion system onboard checkout and monitoring equipment to establish design criteria - Vol. 2
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-119840 , MCR-71-62-VOL-2
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 86
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    Feasibility study of jet-fuel-cooled plug nozzle for afterburning turbojet (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Cooling, coking, construction, and structural characteristics of jet fuel-cooled plug nozzle for afterburning turbojet
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2304 , E-6022
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 87
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    Titanium pump impeller testing Final report (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Ceramic stresscoat burst and performance test of shrouded, diffusion welded titanium pump impellers for liquid hydrogen pump applications
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-103124 , TMR-0115-3141
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 88
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    Qualification evaluation of the tower jettison motor for the Apollo spacecraft program launch escape system (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Qualification tests of tower jettison motors for Apollo spacecraft program launch escape systems
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TN-D-6295 , MSC-S-216
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 89
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    A preliminary investigation of charge-exchange erosion of accelerator grid supports (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Preliminary investigation to eliminate or reduce concentrated charge exchange ion erosion of accelerator grid supports for electron bombardment ion thrustors
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67842 , E-6286
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 90
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    Bombardment thruster investigations at the Lewis Research Center, 1971 (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Research and development of mercury electron bombardment thrusters
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67836 , E-6315
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 91
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    Tests of permanent magnet and superconducting magnet MPD thrusters (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Tests of permanent magnet and superconducting magnet MPD radiation cooled thrustors
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67827
    Format: application/pdf
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  • 92
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    Annular slit colloid thruster research and development (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Research in optimization of performance, and performance characteristics of annular slit colloid thruster
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TN-D-7001 , G-1002
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 93
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    Prospects for a multipurpose solar electric propulsion stage (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Technology review and performance estimates for fixed design multipurpose solar electric propulsion stage
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-67801
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 94
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    Space shuttle low pressure auxiliary propulsion subsystem definition Summary report (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Low pressure oxygen/hydrogen auxiliary propulsion subsystem for space shuttle
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-114945 , MDC-E0293
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 95
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    Quasi-steady MPD propulsion at high power Final technical report (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Quasi-steady MPD propulsion at power levels in range 1 to 10 megawatts
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-111872 , AVSD-0146-71-RR
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 96
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    A study of the use of liquid base foams for jet noise reduction (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Acoustical properties of liquid base foams and application for jet noise reduction
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-1695
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 97
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    Unstart and stall interactions between a turbojet engine and an axisymmetric inlet with 60-percent internal-area contraction (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Effects of turbojet engine unstart on engine operation and characteristics of stall propagation through compressor and inlet system
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2192 , E-5923
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 98
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    Axisymmetric expansion of a plasma in a magnetic nozzle including thermal conduction (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Analysis of axisymmetric expansion of ionized, hot-electron cold ion plasma in magnetic nozzle
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TN-D-6154 , E-5888
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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  • 99
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    Film cooling with injection through holes (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Performance prediction for turbine blade film cooling with injection through holes
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-CR-116376 , AGARD HIGH TEMP. TURBINES JAN. 1971 (SEE N71-17372 07-28)
    Format: text
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  • 100
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    Langmuir probe measurements in a SERT 2 thruster discharge chamber (1971)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: Plasma measurements in SERT 2 spacecraft ion thruster discharge chamber using Langmuir probe
    Schlagwort(e): PROPULSION SYSTEMS
    Materialart: NASA-TM-X-2088 , E-5776
    Format: application/pdf
    Standort Signatur Erwartet Verfügbarkeit
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