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  • PROPULSION SYSTEMS  (52)
  • ASTROPHYSICS
  • 1970-1974  (52)
  • 1955-1959
  • 1972  (52)
  • 11
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    Space tug propulsion system failure mode, effects and criticality analysis (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For purposes of the study, the propulsion system was considered as consisting of the following: (1) main engine system, (2) auxiliary propulsion system, (3) pneumatic system, (4) hydrogen feed, fill, drain and vent system, (5) oxygen feed, fill, drain and vent system, and (6) helium reentry purge system. Each component was critically examined to identify possible failure modes and the subsequent effect on mission success. Each space tug mission consists of three phases: launch to separation from shuttle, separation to redocking, and redocking to landing. The analysis considered the results of failure of a component during each phase of the mission. After the failure modes of each component were tabulated, those components whose failure would result in possible or certain loss of mission or inability to return the Tug to ground were identified as critical components and a criticality number determined for each. The criticality number of a component denotes the number of mission failures in one million missions due to the loss of that component. A total of 68 components were identified as critical with criticality numbers ranging from 1 to 2990.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-61388
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Analysis of a supersonic-combustion rocket concept (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary analysis has been made of a supersonic-combustion rocket engine concept using hydrogen and oxygen propellants. The ejector action of a separate small rocket motor is employed to pump the propellants to high stagnation pressures and supersonic velocities. Therefore complicated heavy turbopumps are eliminated and cooling problems of a sonic throat are reduced. The results of the study show that vacuum specific impulse levels as high as a conventional rocket having the same chamber pressure as the drive motor are possible. The supersonic-combustion rocket would be an attractive alternate for a high-altitude low-thrust conventional rocket operating with a pressure feed propellant system. It would also be a convenient technique for obtaining extremely high thrusts without the need for developing corresponding large turbopumps.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-68020 , E-6825
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Dynamics of a supersonic inlet-engine combination subjected to disturbances in fuel flow and inlet overboard bypass airflow (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An axisymmetric mixed-compression supersonic inlet and a single-spool turbojet engine were dynamically tested at Mach 2.5. The propulsion system was subjected to sweep-frequency sinusoidal disturbances of either inlet overboard bypass airflow. The disturbances were at a logarithmic sweep rate of 1 decade per minute. Dynamic responses were taken of signals throughout the propulsion system. Selected signals were reduced relative to the prime propulsion system parameters. The experimental data are presented in Bode plots. Most of the plots are for a frequency range of 1.0 to 50 hertz.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2558 , E-6115
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    Performance and control study of a low-pressure-ratio turbojet engine for a drone aircraft (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of analog and digital computer studies of a low-pressure-ratio turbojet engine system for use in a drone vehicle are presented. The turbojet engine consists of a four-stage axial compressor, single-stage turbine, and a fixed area exhaust nozzle. Three simplified fuel schedules and a generalized parameter fuel control for the engine system are presented and evaluated. The evaluation is based on the performance of each schedule or control during engine acceleration from a windmill start at Mach 0.8 and 6100 meters to 100 percent corrected speed. It was found that, because of the higher acceleration margin permitted by the control, the generalized parameter control exhibited the best dynamic performance.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2537 , E-6688
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    European auxiliary propulsion, 1972 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The chemical and electric auxiliary propulsion technology of the United Kingdom, France, and West Germany is discussed in detail, and the propulsion technology achievements of Italy, India, Japan, and Russia are reviewed. A comparison is presented of Shell 405 catalyst and a European spontaneous hydrazine catalyst called CNESRO I. Finally, conclusions are drawn regarding future trends in European auxiliary propulsion technology development.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-128328 , JPL-TM-33-555
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 16
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    Optimization of electrostatic dual-grid beam-deflection system (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were performed to minimize accelerator grid erosion of a 5-cm diameter Kaufman ion thruster due to direct beam impingement. Several different screen hole diameters, pillow-shape-square screen holes, and dished screen grids were tried. The optimization was accomplished by copper plating the accelerator grid before testing each grid configuration on a thruster for a 2-hour run. The thruster beam sputtered copper and molybdenum from the accelerator grid where the beam impinged. The observed erosion patterns and measured accelerator currents were used to determine how to modify the accelerator system. The lowest erosion was obtained for a 50-percent open area pillow-shape-square-aperture screen grid, dished 0.043 centimeter convex toward the accelerator grid, which was positioned with the center of the screen grid 0.084 centimeter from the accelerator grid. During this investigation the accelerator current was reduced from 120 to 55 microamperes and was also more uniformly distributed over the area of the accelerator grid.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-68096 , E-7012
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Internal performance of a 10 deg conical plug nozzle with a multispoke primary and translating external shroud (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted in a nozzle static test facility to determine the performance characteristics of a cold-flow, 21.59-centimeter-diameter plug nozzle with a multispoke primary. Two multispoke primary nozzles, a 12-spoke and a 24-spoke, were tested and compared with an annular plug nozzle. The supersonic cruise configurations for both spoke primaries performed about the same, with a gross thrust coefficient of 0.974, a decrease of approximately 1.5 percent from the reference nozzle. The takeoff configuration for the 12-spoke primary had a gross thrust coefficient of 0.957, a decrease of 1.5 percent from the reference nozzle, and the 24-spoke primary had a gross thrust coefficient of 0.95.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2573 , E-6877
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    Completely modular Thermionic Reactor Ion Propulsion System (TRIPS) (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The nuclear reactor powered ion propulsion system described is an advanced completely modularized system which lends itself to development of prototype and/or flight type components without the need for complete system tests until late in the development program. This modularity is achieved in all of the subsystems and components of the electric propulsion system including (1) the thermionic fuel elements, (2) the heat rejection subsystem (heat pipes), (3) the power conditioning modules, and (4) the ion thrusters. Both flashlight and external fuel type in-core thermionic reactors are considered as the power source. The thermionic fuel elements would be useful over a range of reactor power levels. Electrical heated acceptance testing in their flight configuration is possible for the external fuel case. Nuclear heated testing by sampling methods could be used for acceptance testing of flashlight fuel elements. The use of heat pipes for cooling the collectors and as a means of heat transport to the radiator allows early prototype or flight configuration testing of a small module of the heat rejection subsystem as opposed to full scale liquid metal pumps and radiators in a large vacuum chamber. The power conditioner (p/c) is arranged in modules with passive cooling.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-126865 , JPL-TM-33-550
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Evaluation of a pulsed quasi-steady MPD thruster and associated subsystems (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The performance of quasi-steady magnetoplasmadynamic (MPD) thrusters at high power levels is discussed. An axisymmetric configuration is used for the MPD thruster, with various cathode and anode sizes, over a wide range of experimental conditions. Thrust is determined from impulse measurements with current waveforms, while instantaneous measurements are made for all other variables. It is demonstrated that the thrust produced has a predominately self-magnetic origin and is directly proportional to the square of the current. The complete set of impulse measurement data is presented.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-112027 , AVSD-0146-72-RR
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 20
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    Transonic and supersonic test of a Mach 2.65 mixed-compression axisymmetric intake (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The test results describe isolated intake performance between Mach 0.95 and the cruise Mach number of 2.65 at angles of incidence from +5 to -5 deg. Maximum total pressure recoveries of over 94 percent with 10 percent distortion were recorded at the compressor face in the Mach range from 2.65 to 2.4. Typical cruise operating recovery was 91 percent with 13 percent distortion, 7 percent bleed, 5 percent corrected flow stability margin, and 2.2 deg angle-of-incidence tolerance without need for control action. In the started range below Mach 2.4, recoveries were 2 percent to 4 percent lower than the recoveries above Mach 2.4, and the distortion increased to approximately 20 percent. At Mach 0.95 the maximum measured capture flow was 99.4 percent of the theoretical choked value. The recovery was 97.1 percent with less than 10 percent distortion.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-1977
    Format: application/pdf
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