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  • SPACECRAFT PROPULSION AND POWER  (24)
  • 1
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    LeRC rail accelerators - Test designs and diagnostic techniques (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The feasibility of using rail accelerators for various in-space and to-space propulsion applications was investigated. A 1 meter, 24 sq mm bore accelerator was designed with the goal of demonstrating projectile velocities of 15 km/sec using a peak current of 200 kA. A second rail accelerator, 1 meter long with a 156.25 sq mm bore, was designed with clear polycarbonate sidewalls to permit visual observation of the plasma arc. A study of available diagnostic techniques and their application to the rail accelerator is presented. Specific topics of discussion include the use of interferometry and spectroscopy to examine the plasma armature as well as the use of optical sensors to measure rail displacement during acceleration. Standard diagnostics such as current and voltage measurements are also discussed. Previously announced in STAR as N83-35053
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Transactions on Magnetics (ISSN 0018-9464); MAG-20; 324-327
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Rail accelerators for space transportation: An experimental investigation (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental program was conducted at the Lewis Research Center with the objective of investigating the technical feasibility of rail accelerators for propulsion applications. Single-stage, plasma driven rail accelerators of small (4 by 6 mm) and medium (12.5 by 12.5 mm) bores were tested at peak accelerating currents of 50 to 450 kA. Streak-camera photography was used to provide a qualitative description of plasma armature acceleration. The effects of plasma blowby and varying bore pressure on the behavior of plasma armatures were studied.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TP-2571 , E-2754 , NAS 1.60:2571
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Ion Propulsion for Spacecraft (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The theory of the ion-thruster propulsion system is discussed along with the Space Electric Rocket Test 1 and 2. The use of electric propulsion for stationkeeping and attitude control functions of geosynchronous satellites is described, and a comparison of thruster systems is presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-79502
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Rail accelerator research at Lewis Research Center (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A rail accelerator was chosen for study as an electromagnetic space propulsion device because of its simplicity and existing technology base. The results of a mission feasibility study using a large rail accelerator for direct launch of ton-size payloads from the Earth's surface to space, and the results of initial tests with a small, laboratory rail accelerator are presented. The laboratory rail accelerator has a bore of 3 by 3 mm and has accelerated 60 mg projectiles to velocities of 300 to 1000 m/s. Rail materials of Cu, W, and Mo were tested for efficiency and erosion rate.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-83015 , E-1449 , NAS 1.15:83015 , AIAA PAPER 82-1938 , Intern. Electric Propulsion Conf; Nov 17, 1982 - Nov 19, 1982; New Orleans
    Format: application/pdf
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  • 5
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    SERT II 1980 extended flight thruster experiments (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The SERT II spacecraft, launched in 1970, has been maintained in an operational, but intermittent status since 1971. This paper presents the flight results obtained from mid 1979 through December 1980. Near continuous solar power in 1979 and 1980 has enabled long periods of thruster endurance testing. Three of four propellant tanks have been exhausted with no significant change in thruster system operation before being empty. A new plasma mode thrust has been characterized and direct thrust measurements obtained. Other tests, including beam neutralization by various neutralizer sources, give insight to electron conduction across plasmas in space and provide a basis to model neutralization of thruster arrays.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 81-0665 , International Electric Propulsion Conference; Apr 21, 1981 - Apr 23, 1981; Las Vegas, NV; US
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  • 6
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    Evolution of the 1-mlb mercury ion thruster subsystem (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A general description and review of the auxiliary Electric Propulsion program, which led to the present 1-mlb (4.5 mN) thruster system, is presented. The developmental history, performance, and major lifetests of each component of the system are traced over the past 10 years. Major components include the 8-cm diameter ion thruster, the power processor, and the propellant reservoir and distribution system.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-711B , International Electric Propulsion Conference; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; US
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    NASA TECHNICAL REPORTS
  • 7
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    Status of SERT II spacecraft and ion thrusters - 1978 (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The historical record of the SERT II spacecraft and ion thruster systems for 8 years since the February 1970 launch is reviewed. The original SERT II mission, one year duration, was planned with the spacecraft in a continuous sunlight orbit to provide continuous solar power. An extended mission, using intermittent power available from an earth shadowed orbit has been performed during the past 5 years while waiting for the orbit to change again to continuous sunlight in early 1979. Continuous thruster testing is planned in 1979. Both spacecraft and ion thruster systems are near-fully functional when the solar array is illuminated. Thruster system 2 is fully operational. Thruster system 1 continues to demonstrate relight capability, but the high-voltage-grid short remains.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 78-662 , International Electric Propulsion Conference; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; US
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    NASA TECHNICAL REPORTS
  • 8
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    Evolution of the 1-mlb mercury ion thruster subsystem (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The developmental history, performance, and major lifetests of each component of the present 1-mlb (4.5 mN) thruster system are traced over the past 10 years. The 1-mlb thruster subsystem consists of an 8 cm diameter ion thruster mounted on 2 axis gimbals, a mercury propellant tank, a power electronics unit, a controller/digital interface unit, and necessary electrical harnesses plus propellant tankage and feed lines.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-73733 , E-9278 , Intern. Elec. Propulsion Conf.; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; United States
    Format: application/pdf
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  • 9
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    Status of SERT II spacecraft and ion thrusters, 1978 (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The historical record of the SERT 2 spacecraft and ion thruster systems for 8 years since the February 1970 launch is reviewed. The original SERT 2 mission, one year duration, was planned with the spacecraft in a continuous sunlight orbit to provide continuous solar power. An extended mission, using intermittent power available from an earth shadowed orbit was performed during the past 5 years while waiting for the orbit to change again to continuous sunlight in early 1979. Continuous thruster testing is planned in 1979. Both spacecraft and ion thruster systems are near-fully functional when the solar array is illuminated. Thruster system 2 is fully operational. Thruster system 1 continues to demonstrate relight capability, but the high-voltage-grid short remains.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-78827 , E-9531 , Intern. Elec. Propulsion Conf.; Apr 25, 1978 - Apr 27, 1978; San Diego, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Long lifetime hollow cathodes for 30-cm mercury ion thrusters (1976)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation of hollow cathodes for 30-cm Hg bombardment thrusters was carried out. Both main and neutralizer cathode configurations were tested with both rolled foil inserts coated with low work function material and impregnated porous tungsten inserts. Temperature measurements of an impregnated insert at various positions in the cathode were made. These, along with the cathode thermal profile are presented. A theory for rolled foil and impregnated insert operation and lifetime in hollow cathodes is developed. Several endurance tests, as long as 18000 hours at emission currents of up to 12 amps were attained with no degradation in performance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-X-73523 , E-8937 , Intern. Elec. Propulsion Conf.; Nov 15, 1976 - Nov 17, 1976; Key Biscayne, FL; United States
    Format: application/pdf
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