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  • SPACECRAFT PROPULSION AND POWER  (16)
  • Populus deltoides  (3)
  • 1985-1989  (19)
  • 1940-1944
  • 11
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    Performance and lifetime assessment of MPD arc thruster technology (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A summary of performance and lifetime characteristics of pulsed and steady-state magnetoplasmadynamic (MPD) thrusters is presented. The technical focus is on cargo vehicle propulsion for exploration-class missions to the Moon and Mars. Relatively high MPD thruster efficiencies of 0.43 and 0.69 have been reported at about 5000 s specific impulse using hydrogen and lithium, respectively. Efficiencies of 0.10 to 0.35 in the 1000 to 4500 s specific impulse range have been obtained with other propellants (e.g., Ar, NH3, N2). Thermal efficiency data in excess of 0.80 at MW power levels using pulsed thrusters indicate the potential of high MPD thruster performance. Extended tests of pulsed and steady-state MPD thrusters yield total impulses at least two to three orders of magnitude below that necessary for cargo vehicle propulsion. Performance tests and diagnostics for life-limiting mechanisms of megawatt-class thrusters will require high fidelity test stands which handle in excess of 10 kA and a vacuum facility whose operational pressure is less than 3 x 10 to the -4 torr.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-101293 , E-4274 , NAS 1.15:101293 , AIAA PAPER 88-3211
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 12
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    Performance and lifetime assessment of MPD arc thruster technology (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A summary of performance and lifetime characteristics of pulsed and steady-state magnetoplasmadynamic (MPD) thrusters is presented. The technical focus is on cargo vehicle propulsion for exploration-class missions to the Moon and Mars. Relatively high MPD thruster efficiencies of 0.43 and 0.69 have been reported at about 5000 s specific impulse using hydrogen and lithium, respectively. Efficiencies of 0.10 to 0.35 in the 1000 to 4500 s specific impulse range have been obtained with other propellants (e.g., Ar, NH3, N2). Thermal efficiency data in excess of 0.80 at MW power levels using pulsed thrusters indicate the potential of high MPD thruster performance. Extended tests of pulsed and steady-state MPD thrusters yield total impulses at least two to three orders of magnitude below that necessary for cargo vehicle propulsion. Performance tests and diagnostics for life-limiting mechanisms of megawatt-class thrusters will require high fidelity test stands which handle in excess of 10 kA and a vacuum facility whose operational pressure is less than 3 x 10 to the -4 torr.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 88-3211
    Format: text
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    NASA TECHNICAL REPORTS
  • 13
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    Space station propulsion (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two propulsion systems have been selected for the space station: gaseous H/O rockets for high thrust applications and the multipropellant resistojets for low thrust needs. These two thruster systems integrate very well with the fluid systems on the space station, utilizing waste fluids as their source of propellant. The H/O rocket will be fueled by electrolyzed water and the resistojets will use waste gases collected from the environmental control system and the various laboratories. The results are presented of experimental efforts with H/O and resistojet thrusters to determine their performance and life capability, as well as results of studies to determine the availability of water and waste gases.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-100216 , E-3825 , NAS 1.15:100216
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    NASA TECHNICAL REPORTS
  • 14
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    2000-hour cyclic endurance test of a laboratory model multipropellant resistojet (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The technological readiness of a long-life multipropellant resistojet for space station auxiliary propulsion is demonstrated. A laboratory model resistojet made from grain-stabilized platinum served as a test bed to evaluate the design characteristics, fabrication methods, and operating strategies for an engineering model multipropellant resistojet developed under contract by the Rocketdyne Division of Rockwell International and Technion Incorporated. The laboratory model thruster was subjected to a 2000-hr, 2400-thermal-cycle endurance test using carbon dioxide propellant. Maximum thruster temperatures were approximately 1400 C. The post-test analyses of the laboratory model thruster included an investigation of component microstructures. Significant observations from the laboratory model thruster are discussed as they relate to the design of the engineering model thruster.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-0993
    Format: text
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    NASA TECHNICAL REPORTS
  • 15
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    Preliminary performance characterizations of an engineering model multipropellant resistojet for space station application (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Presented are the results of a program to describe the operational characteristics of an engineering model multipropellant resistojet for application as an auxiliary propulsion system for the space station. Performance was measured on hydrogen, helium, methane, water (steam), nitrogen, air, argon, and carbon dioxide. Thrust levels ranged from 109 to 355 mN, power levels ranged from 167 to 506 W, and specific impulse values ranged from 93 to 385 sec, depending on the propellant, chamber pressure, and heater current level selected. Detailed thermal maps of the heater and heat exchanger were also obtained for operation with carbon dioxide.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2120
    Format: text
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    NASA TECHNICAL REPORTS
  • 16
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    Electromagnetic emission experiences using electric propulsion systems - A survey (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: As electric propulsion systems become ready to integrate with spacecraft systems, the impact of propulsion system radiated emissions are of significant interest. Radiated emissions from electromagnetic, electrostatic, and electrothermal systems have been characterized and results synopsized from the literature describing 21 space flight programs. Electromagnetic radiated emission results from ground tests and flight experiences are presented with particular attention paid to the performance of spacecraft subsystems and payloads during thruster operations. The impacts to transmission of radio frequency signals through plasma plumes are also reviewed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2028
    Format: text
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    NASA TECHNICAL REPORTS
  • 17
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    Water-propellant resistojets for man-tended platforms (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The selection of a propulsion system for a man-tended platform has been influenced by the planned use of resistojets for drag make-up on the manned Space Station. For that application a resistojet has been designed that is capable of operation with a wide variety of propellants, including water. The reasons for the selection of water as the propellant and the performance of water as a propellant are discussed. The man-tended platform and its mission requirements are described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 87-259
    Format: text
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    NASA TECHNICAL REPORTS
  • 18
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    Performance of a 100 kW class applied field MPD thruster (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Performance of a 100 kW, applied field magnetoplasmadynamic (MPD) thruster was evaluated and sensitivities of discharge characteristics to arc current, mass flow rate, and applied magnetic field were investigated. Thermal efficiencies as high as 60 percent, thrust efficiencies up to 21 percent, and specific impulses of up to 1150 s were attained with argon propellant. Thrust levels up to 2.5 N were directly measured with an inverted pendulum thrust stand at discharge input powers up to 57 kW. It was observed that thrust increased monotonically with the product of arc current and magnet current.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-102312 , E-5006 , NAS 1.15:102312 , AIAA PAPER 89-2710 , Joint Propulsion Conference; Jul 10, 1989 - Jul 12, 1989; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Test facility and preliminary performance of a 100 kW class MPD thruster (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A 260 kW magnetoplasmadynamic (MPD) thruster test facility was assembled and used to characterize thrusters at power levels up to 130 kW using argon and helium propellants. Sensitivities of discharge characteristics to arc current, mass flow rate, and applied magnetic field were investigated. A thermal efficiency correlation developed by others for low power MPD thrusters defined parametric guidelines to minimize electrode losses in MPD thrusters. Argon and helium results suggest that a parameter defined as the product of arc voltage and the square root of the mass flow rate must exceed .7 V-kg(1/2)-s(-1/2) in order to obtain thermal efficiencies in excess of 60 percent.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-102021 , E-4742 , NAS 1.15:102021 , JANNAF Propulsion Meeting; May 23, 1989 - May 25, 1989; Cleveland, OH; United States
    Format: application/pdf
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