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  • 1995-1999  (5)
  • 1
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    Electrolysis Propulsion for Spacecraft Applications (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Electrolysis propulsion has been recognized over the last several decades as a viable option to meet many satellite and spacecraft propulsion requirements. This technology, however, was never used for in-space missions. In the same time frame, water based fuel cells have flown in a number of missions. These systems have many components similar to electrolysis propulsion systems. Recent advances in component technology include: lightweight tankage, water vapor feed electrolysis, fuel cell technology, and thrust chamber materials for propulsion. Taken together, these developments make propulsion and/or power using electrolysis/fuel cell technology very attractive as separate or integrated systems. A water electrolysis propulsion testbed was constructed and tested in a joint NASA/Hamilton Standard/Lawrence Livermore National Laboratories program to demonstrate these technology developments for propulsion. The results from these testbed experiments using a I-N thruster are presented. A concept to integrate a propulsion system and a fuel cell system into a unitized spacecraft propulsion and power system is outlined.
    Keywords: Atomic and Molecular Physics
    Type: NASA-TM-113157 , NAS 1.15:113157 , E-10907 , AIAA Paper 97-2948 , Joint Propulsion Conference and Exhibit; Jul 06, 1997 - Jul 09, 1997; Seattle, WA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A Performance Comparison of Pulsed Plasma Thruster Electrode Configurations (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Pulsed plasma thrusters are currently planned on two small satellite missions and proposed for a third. In these missions, the pulsed plasma thruster's unique characteristics will be used variously to provide propulsive attitude control, orbit raising, translation, and precision positioning. Pulsed plasma thrusters are attractive for small satellite applications because they are essentially stand alone devices which eliminate the need for toxic and/or distributed propellant systems. Pulsed plasma thrusters also operate at low power and over a wide power range without loss of performance. As part of the technical development required for the noted missions, an experimental program to optimize performance with respect to electrode configuration was undertaken. One of the planned missions will use pulsed plasma thrusters for orbit raising requiring relatively high thrust and previously tested configurations did not provide this. Also, higher capacitor energies were tested than previously tried for this mission. Multiple configurations were tested and a final configuration was selected for flight hardware development. This paper describes the results of the electrode optimization in detail.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-97-206305 , E-11002 , NAS 1.15:206305 , IEPC-97-127 , International Electric Propulsion Conference; Aug 24, 1997 - Aug 28, 1997; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Multi-Axis Thrust Measurements of the EO-1 Pulsed Plasma Thruster (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Pulsed plasma thrusters are low thrust propulsive devices which have a high specific impulse at low power. A pulsed plasma thruster is currently scheduled to fly as an experiment on NASA's Earth Observing-1 satellite mission. The pulsed plasma thruster will be used to replace one of the reaction wheels. As part of the qualification testing of the thruster it is necessary to determine the nominal thrust as a function of charge energy. These data will be used to determine control algorithms. Testing was first completed on a breadboard pulsed plasma thruster to determine nominal or primary axis thrust and associated propellant mass consumption as a function of energy and then later to determine if any significant off-axis thrust component existed. On conclusion that there was a significant off-axis thrust component with the bread-board in the direction of the anode electrode, the test matrix was expanded on the flight hardware to include thrust measurements along all three orthogonal axes. Similar off-axis components were found with the flight unit.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-1999-209396 , NAS 1.15:209396 , E-11830 , AIAA Paper 99-2290 , Joint Propulsion; Jun 20, 1999 - Jun 24, 1999; Los Angeles, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A performance comparison of two small rocket nozzles (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental study was conducted on two small rockets (110 N thrust class) to directly compare a standard conical nozzle with a bell nozzle optimized for maximum thrust using the Rao method. In large rockets, with throat Reynolds numbers of greater than 1 x 10(exp 5), bell nozzles outperform conical nozzles. In rockets with throat Reynolds numbers below 1 x 10(exp 5), however, test results have been ambiguous. An experimental program was conducted to test two small nozzles at two different fuel film cooling percentages and three different chamber pressures. Test results showed that for the throat Reynolds number range from 2 x 10(exp 4) to 4 x 10(exp 4), the bell nozzle outperformed the conical nozzle. Thrust coefficients for the bell nozzle were approximately 4 to 12 percent higher than those obtained with the conical nozzle. As expected, testing showed that lowering the fuel film cooling increased performance for both nozzle types.
    Keywords: Spacecraft Design, Testing and Performance
    Type: NASA-TM-107285 , NAS 1.15:107285 , AIAA Paper 96-2582 , E-10360 , Joint Propulsion Conference; Jul 01, 1996 - Jul 03, 1996; Lake Buena Vista, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Pulsed Plasma Thruster Contamination (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Pulsed Plasma Thrusters (PPT's) are currently baselined for the Air Force Mightysat II.1 flight in 1999 and are under consideration for a number of other missions for primary propulsion, precision positioning, and attitude control functions. In this work, PPT plumes were characterized to assess their contamination characteristics. Diagnostics included planar and cylindrical Langmuir probes and a large number of collimated quartz contamination sensors. Measurements were made using a LES 8/9 flight PPT at 0.24, 0.39, 0.55, and 1.2 m from the thruster, as well as in the backflow region behind the thruster. Plasma measurements revealed a peak centerline ion density and velocity of approx. 6 x 10(exp 12) cm(exp -3) and 42,000 m/s, respectively. Optical transmittance measurements of the quartz sensors after 2 x 10(exp 5) pulses showed a rapid decrease in plume contamination with increasing angle from the plume axis, with a barely measurable transmittance decrease in the ultraviolet at 90 deg. No change in optical properties was detected for sensors in the backflow region.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-107328 , E-10434 , NAS 1.15:107328 , AIAA Paper 96-2729 , Joint Propulsion Conference; Jul 01, 1996 - Jul 03, 1996; Lake Buena Vista, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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