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  • 1
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    Fundamentals of Mathematical Physics (1968)
    Institute of Physics
    Details
    Publication Date: 1968-03-01
    Print ISSN: 0031-9112
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 2
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    Group Theory and Its Physical Applications (1967)
    Institute of Physics
    Details
    Publication Date: 1967-02-01
    Print ISSN: 0031-9112
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 3
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    Dynamics (1966)
    Institute of Physics
    Details
    Publication Date: 1966-08-01
    Print ISSN: 0031-9112
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 4
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    Acceleration = v2/r (1966)
    Institute of Physics
    Details
    Publication Date: 1966-09-01
    Print ISSN: 0031-9120
    Electronic ISSN: 1361-6552
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 5
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    ATS-6 - Cesium bombardment engine north-south stationkeeping experiment (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Two 0.004 N thrust cesium bombardment ion thrustors have been developed and used for north-south stationkeeping in the geostationary Applications Technology Satellite-6 (ATS-6). The thrustor subsystems are mounted on the north and south faces of the earth viewing module such that 0.0026 N of thrust is applied normal to the orbit plane and 0.0036 N is applied radially upward. The change in the orbit inclination of the satellite is maintained at zero by operating the two thrustors alternately so that their thrust components, normal to the orbital plane, are symmetrically applied about the nodal crossings. Initial operation of the thrustors was successful. There was no interference with the satellite communications systems and the predicted spacecraft operating potential was verified. Subsequent trials failed due to a defect in the operation of the propellant reservoirs in zero g. A feed line valve is under development to correct this difficulty.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Transactions on Aerospace and Electronic Systems; AES-11; Nov. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    The cesium bombardment engine north-south stationkeeping experiment on ATS-6 (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Two one millipound-thrust cesium bombardment ion thrusters have been developed and integrated on the ATS-F spacecraft for the purpose of demonstrating compatible north-south stationkeeping of a synchronous communication satellite. Preliminary operation of the two thrusters on ATS-6 was completely successful on the first run of each. In addition to verifying operation, the principal accomplishments were the demonstration of a total absence of interference with the communications systems, verification of the predicted spacecraft operating potential, demonstration of compatibility with the star tracker, and demonstration of spacecraft attitude by thrust vectoring. Subsequent attempts to operate the thrusters have not been successful. Analysis indicates that the problem is associated with operation of the propellant reservoirs in zero-g.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-363 , American Institute of Aeronautics and Astronautics, Electric Propulsion Conference; Mar 19, 1975 - Mar 21, 1975; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Results of the mission profile life test (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Seven J series 30-cm diameter thrusters have been tested in segments of up to 5,070 hr, for 14,541 hr in the Mission Profile Life Test facility. Test results have indicated the basic thruster design to be consistent with the lifetime goal of 15,000 hr at 2-A beam. The only areas of concern identified which appear to require additional verification testing involve contamination of mercury propellant isolators, which may be due to facility constituents, and the ability of specially covered surfaces to contain sputtered material and prevent flake formation. The ability of the SCR, series resonant inverter power processor to operate the J series thruster and autonomous computer control of the thruster/processor system were demonstrated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 82-1905 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Operational summary of an electric propulsion long term test facility (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An automated test facility capable of simultaneously operating three 2.5 kW, 30-cm mercury ion thrusters and their power processors is described, along with a test program conducted for the documentation of thruster characteristics as a function of time. Facility controls are analog, with full redundancy, so that in the event of malfunction the facility automaticcally activates a backup mode and notifies an operator. Test data are recorded by a central data collection system and processed as daily averages. The facility has operated continuously for a period of 37 months, over which nine mercury ion thrusters and four power processor units accumulated a total of over 14,500 hours of thruster operating time.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: AIAA PAPER 82-1903 , Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference; Nov 17, 1982 - Nov 19, 1982; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Analysis and design of ion thrusters for large space systems (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This study undertakes the analysis and conceptual design of a 0.5 Newton electrostatic ion thruster suitable for use on large space system missions in the next decade. Either argon or xenon gas shall be used as propellant. A 50 cm diameter discharge chamber was selected to meet stipulated performance goals. The discharge plasma is contained at the boundary by a periodic structure of alternating permanent magnets generating a series of line cusps. Anode strips between the magnets collect Maxwellian electrons generated by a central cathode. Ion extraction utilizes either two or three grid optics at the user's choice. An extensive analysis was undertaken to investigate optics behavior in the high power environment of this large thruster. A plasma bridge neutralizer operating on inert gas provides charge neutralizing electrons to complete the design. The resulting conceptual thruster and the necessary power management and control requirements are described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165160 , NAS 1.26:165160
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Results of the Mission Profile Life Test first test segment - Thruster J1 (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A series of long term test segments of 30 cm diameter mercury bombardment thrusters is being conducted as the Mission Profile Life Test. The first 4000 hour segment has been completed with the J series thruster, J1. Thruster and power processing units were controlled by computer with software algorithms governing normal functions of startup, throttle, and shutdown as well as automatically handling a variety of off-normal conditions. Thruster operation includes a discussion of the test chronology describing notable events and their significance. Post-test examination provides insight into thruster lifetime. Results are consistent with mission requirements of 15,000 hours at 2A
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 81-0716 , International Electric Propulsion Conference; Apr 21, 1981 - Apr 23, 1981; Las Vegas, NV; US
    Format: text
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    NASA TECHNICAL REPORTS
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