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  • 1
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    Kapton charging characteristics: Effects of material thickness and electron-energy distribution (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Charging characteristics of polyimide (Kapton) of varying thicknesses under irradiation by a very-low-curent-density electron beam, with the back surface of the sample grounded are reported. These charging characteristics are in good agreement with a simple analytical model which predicts that in thin samples at low current density, sample surface potential is limited by conduction leakage through the bulk material. The charging of Kapton in a low-current-density electron beam in which the beam energy was modulated to simulate Maxwellian and biMaxwellian distribution functions is measured.
    Keywords: NONMETALLIC MATERIALS
    Type: NASA. Lewis Research Center Spacecraft Environ. Interactions Technol., 1983; p 547-558
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Evaluation of charge control techniques on spacecraft thermal surfaces (electrostatic discharge study) (1980)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The charging and discharging characteristics of various dielectric materials commonly used on spacecraft were tested. The experimental apparatus and the calculations used to analyze the data generated during the testing are described. The test technique, results, and analysis used are presented. Indium tin oxide coated Teflon, Kapton, and quartz do not charge significantly. CTL 15 white paint shows no large charge build up. Pinholes in Teflon and Kapton increase the leakage through the sample and reduce the energy released in an arc. Conductive grids in Teflon and Kapton reduce the arc energy by two orders of magnitude over untreated samples. Extreme low temperatures (-195 C) do not significantly increase the arc energy of the gridded sample.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Lewis Research Center Spacecraft Charging Technol., 1980; p 320-341
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Retrofit and verification test of a 30-cm ion thruster (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Twenty modifications were found to be necessary and were approved by design review. These design modifications were incorporated in the thruster documents (drawings and procedures) to define the J series thruster. Sixteen of the design revisions were implemented in a 900 series thruster by retrofit modification. A standardized set of test procedures was formulated, and the retrofit J series thruster design was verified by test. Some difficulty was observed with the modification to the ion optics assembly, but the overall effect of the design modification satisfies the design objectives. The thruster was tested over a wide range of operating parameters to demonstrate its capabilities.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-165233
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Electric propulsion - characteristics, applications, and status (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A comparative review of the principles of ion thruster and chemical rocket operations is presented. The 30cm mercury ion thruster development and the specifications imposed on it by the Solar Electric propulsion System program are discussed. The 30cm thruster operating range, efficiency, wear out lifetime, and interface requirements are described.
    Keywords: LAUNCH VEHICLES AND SPACE VEHICLES
    Type: NASA-TM-81630 , E-640
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Deflectable beam linear strip cesium contact ion thruster system (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Deflectable dual beam, linear strip cesium contact, ion thruster system design and performance testing
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-72989
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Engineering Model 8-cm Thruster System (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Development of an Engineering Model 8-cm Mercury Ion Thruster System for Satellite Control has been successfully completed. This system operates at a specific impulse in excess of 2600 sec, produces a thrust of 5 mN with a total input power of 165 W; it has a dry mass of 16.6 kg and a mercury-propellant-reservoir capacity of 8.75 kg. This paper summarizes the development work, the system characteristics and performance, and the testing undertaken to verify the design.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-646 , International Electric Propulsion Conference; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; US
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    One-millipound mercury ion thruster (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A mercury ion thruster has been developed for efficient operation at the nominal 1-mlb thrust level with a specific impulse of about 3,000 sec and a total power consumption of about 120 W. At a beam voltage of 1,200 V and beam current of 72 mA, the discharge chamber operates with a propellant efficiency of 93.8% at an ion-generation energy of 276 eV/ion. The 8-cm diameter thruster advances proven component technology to assure the capability for thruster operation over an accumulated beam-on time in excess of 20,000 hours with a capability for 10,000 on-off duty cycles. Discharge chamber optimization has combined stable current-voltage characteristics with high performance efficiency by careful placement of the discharge cathode near the location of a magnetic-field zero just upstream of the thruster endplate.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 75-386 , 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
  • 8
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    Dual deflectable beam strip engine development. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper describes a dual beam thruster that has been designed, constructed, and tested. The system is suitable for two-axes attitude control and is comprised of two orthogonal strips, each capable of producing 0.30 mlb thrust and beam deflections of more than plus or minus 20 deg. The nominal specific impulse for the thruster is 5000 sec, and the thrust level from each strip can be varied from 0 to 100%. Neutralizer filaments that were developed and life tested over 2000 hours producing more than 40 mA of electron emission per watt of input power are also discussed. The system power required for clean ionizers is approximately 200 W.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 72-494 , American Institute of Aeronautics and Astronautics, Electric Propulsion Conference; Apr 17, 1972 - Apr 19, 1972; Bethesda, MD
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Modularized ion thruster (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A modularized ion thruster system was developed for space-propulsion applications. Separate discharge chamber modules (DCMs) were optimized for operation at the thrust levels of T = 0.5 mlb and T = 2 mlb to accommodate the extended thrust range. These optimizations included modifications in the discharge-chamber components and the incorporation of ion machined accelerators in the beam-extraction systems. Performance of the optimized modules are summarized.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-134667
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Ionizer surface protection techniques (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Metallic coating technique for porous tungsten ionizer surface of ion thruster
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-72730
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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