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  • 1
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    NASA spacecraft propulsion activities (1997)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: The NASA's activities in the development of spacecraft propulsion systems are reviewed, with emphasis on program directions and recent progress made in this domain. The recent trends towards the use of smaller spacecraft and launch vehicles call for new onboard propulsion systems. The NASA's efforts are conducted within the framework of the onboard propulsion program. The research and development work carried out in relation to the different propulsion system technologies are considered: electromagnetic systems; electrostatic systems; electrothermal systems; bipropellant systems; and monopropellant systems.
    Keywords: Spacecraft Propulsion and Power
    Type: ; 35-44
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    HAN-Based Monopropellant Propulsion System with Applications (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: NASA is developing a new monopropellant propulsion system for small, cost-driven spacecraft with AV requirements in the range of 10-150 m/sec. This system is based on a hydroxylammonium nitrate (HAN)/water/fuel monopropellant blend which is extremely dense, environmentally benign, and promises good performance and simplicity. State-of-art (SOA) small spacecraft typically employ either hydrazine or high pressure stored gas. Herein, a 'typical' small satellite bus is used to illustrate how a HAN-based monopropellant propulsion system fulfills small satellite propulsion requirements by providing mass and/or volume savings of SOA hydrazine monopropellants with the cost benefits of a stored nitrogen gas.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-107407 , NAS 1.15:107407 , E-10619
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Experimental performance of a high-area-ratio rocket nozzle at high combustion chamber pressure (1996)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental investigation was conducted to determine the thrust coefficient of a high-area-ratio rocket nozzle at combustion chamber pressures of 12.4 to 16.5 MPa (1800 to 2400 psia). A nozzle with a modified Rao contour and an expansion area ratio of 1025:1 was tested with hydrogen and oxygen at altitude conditions. The same nozzle, truncated to an area ratio of 440:1, was also tested. Values of thrust coefficient are presented along with characteristic exhaust velocity efficiencies, nozzle wall temperatures, and overall thruster specific impulse.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TP-3576 , NAS 1.60:3576 , E-9849
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Performance Evaluation of a 50kW Hall Thruster (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An experimental investigation was conducted on a laboratory model Hall thruster designed to operate at power levels up to 50 kW. During this investigation the engine's performance was characterized over a range of discharge currents from 10 to 36 A and a range of discharge voltages from 200 to 800 V Operating on the Russian cathode a maximum thrust of 966 mN was measured at 35.6 A and 713.0 V. This corresponded to a specific impulse of 3325 s and an efficiency of 62%. The maximum power the engine was operated at was 25 kW. Additional testing was conducted using a NASA cathode designed for higher current operation. During this testing, thrust over 1 N was measured at 40.2 A and 548.9 V. Several issues related to operation of Hall thrusters at these high powers were encountered.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-1999-209447 , NAS 1.15:209447 , E-11939 , AIAA Paper 99-0457 , 37th Aerospace Sciences Meeting; Jan 11, 1999 - Jan 19, 1999; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Performance of a FAKEL K10K Resistojet (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A model K10K resistojet produced by FAKEL Enterprise was evaluated at steady-state conditions with both nitrogen and xenon propellants. Performance and operational characteristics were documented for cold gas and heater power levels up to 8 W at mass flow rates from 0.02 to 0.2 g/s. Maximum specific impulses of 84 s on nitrogen and 49 s on xenon were achieved at the highest specific power levels tested.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-113127 , NAS 1.15:113127 , AIAA Paper 97-3059 , E-10897 , Joint Propulsion; Jul 06, 1997 - Jul 09, 1997; Seattle, WA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Test Results of a 200 W Class Hall Thruster (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The performance of a 200 W class Hall thruster was evaluated. Performance measurements were taken at power levels between 90 W and 250 W. At the nominal 200 W design point, the measured thrust was 11.3 mN. and the specific impulse was 1170 s excluding cathode flow in the calculation. A laboratory model 3 mm diameter hollow cathode was used for all testing. The engine was operated on laboratory power supplies in addition to a breadboard power processing unit fabricated from commercially available DC to DC converters.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-1999-209449 , NAS 1.15:209449 , AIAA Paper 98-3792 , E-11941 , Joint Propulsion Conference; Jul 13, 1998 - Jul 15, 1998; Cleveland, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Preliminary Evaluation of a 10 kW Hall Thruster (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A 10 kW Hall thruster was characterized over a range of discharge voltages from 300-500 V and a range of discharge currents from 15-23 A. This corresponds to power levels from a low of 4.6 kW to a high of 10.7 kW. Over this range of discharge powers, thrust varied from 278 mN to 524 mN, specific impulse ranged from 1644 to 2392 seconds, and efficiency peaked at approximately 59%. A continuous 40 hour test was also undertaken in an attempt to gain insight with regard to long term operation of the engine. For this portion of the testing the thruster was operated at a discharge voltage of 500 V and a discharge current of 20 A. Steady-state temperatures were achieved after 3-5 hrs and very little variation in performance was detected.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM-1999-209075 , NAS 1.15:209075 , AIAA Paper 99-0456 , E-11636 , Aerospace Sciences; Jan 11, 1999 - Jan 14, 1999; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    High-Area-Ratio Rocket Nozzle at High Combustion Chamber Pressure: Experimental and Analytical Validation (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Experimental data were obtained on an optimally contoured nozzle with an area ratio of 1025:1 and on a truncated version of this nozzle with an area ratio of 440:1. The nozzles were tested with gaseous hydrogen and liquid oxygen propellants at combustion chamber pressures of 1800 to 2400 psia and mixture ratios of 3.89 to 6.15. This report compares the experimental performance, heat transfer, and boundary layer total pressure measurements with theoretical predictions of the current Joint Army, Navy, NASA, Air Force (JANNAF) developed methodology. This methodology makes use of the Two-Dimensional Kinetics (TDK) nozzle performance code. Comparisons of the TDK-predicted performance to experimentally attained thrust performance indicated that both the vacuum thrust coefficient and the vacuum specific impulse values were approximately 2.0-percent higher than the turbulent prediction for the 1025:1 configurations, and approximately 0.25-percent higher than the turbulent prediction for the 440:1 configuration. Nozzle wall temperatures were measured on the outside of a thin-walled heat sink nozzle during the test fittings. Nozzle heat fluxes were calculated front the time histories of these temperatures and compared with predictions made with the TDK code. The heat flux values were overpredicted for all cases. The results range from nearly 100 percent at an area ratio of 50 to only approximately 3 percent at an area ratio of 975. Values of the integral of the heat flux as a function of nozzle surface area were also calculated. Comparisons of the experiment with analyses of the heat flux and the heat rate per axial length also show that the experimental values were lower than the predicted value. Three boundary layer rakes mounted on the nozzle exit were used for boundary layer measurements. This arrangement allowed total pressure measurements to be obtained at 14 different distances from the nozzle wall. A comparison of boundary layer total pressure profiles and analytical predictions show good agreement for the first 0.5 in. from the nozzle wall; but the further into the core flow that measurements were taken, the more that TDK overpredicted the boundary layer thickness.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TP-1999-208522 , NAS 1.60:208522 , E-11265
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    HAN-based monopropellant assessment for spacecraft (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The growing cost of space missions, the need for increased mission performance, and concerns associated with environmental issues are changing rocket design and propellant selection criteria. Whereas a propellant's performance was once defined solely in terms of specific impulse and density, now environmental safety, operability, and cost are considered key drivers. Present emphasis on these considerations has heightened government and commercial launch sector interest in Hydroxylammonium Nitrate (HAN)-based liquid propellants as options to provide simple, safe, reliable, low cost, and high performance monopropellant systems.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TM-107287 , E-10362 , NAS 1.15:107287 , AIAA Paper 96-2863 , 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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