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  • Other Sources  (133)
  • SPACECRAFT PROPULSION AND POWER
  • 1980-1984  (133)
  • 1965-1969
  • 1950-1954
  • 1983  (133)
  • 1
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    Photovoltaic conversion of laser to electrical power (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Transmission of power in space using lasers will require devices for converting the laser power to electrical power. One such type of device for accomplishing this is the photovoltaic converter. This paper reviews photovoltaic converters and their application for conversion of monochromatic laser power to electrical power. Laser power densities greater than 1000 W/sq cm are considered. For a converter operated at 300 K a lower bandgap limit of 0.67 eV (1.80 micron) is defined. For ideal conditions, an efficiency of 47.8 percent is calculated for Nd/Liquid laser radiation incident on an Si converter. Several types of photovoltaic converters are discussed. Series resistance is identified as a major problem. Vertical multijunction converters are the most promising photovoltaic devices for use as laser to electric power converters.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 2
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    Space power system utilizing Fresnel lenses for solar power and also thermal energy storage (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A solar power plant suitable for earth orbits passing through Van Allen radiation belts is described. The solar-to-electricity conversion efficiency is estimated to be around 9 percent, and the expected power-to-weight ratio is competitive with photovoltaic arrays. The system is designed to be self-contained, to be indifferent to radiation belt exposures, store energy for periods when the orbiting system is in earth shadow (so that power generation is contant), have no moving parts and no working fluids, and be robust against micrometeorite attack. No electrical batteries are required.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 3
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    Development of a rotary power transformer and inverter drive for spacecraft (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Many future satellites and spacecraft with spun and despun configurations will require the transfer of power across rotating interfaces in lieu of slip-rings and/or flexures. This is particularly true of spacecraft that have to demonstrate a long life expectancy. The rotary transformer has the desirable characteristics of high reliability and low noise, which qualify it as a potential replacement for slip rings. Development of a rotary power transformer follows the successful completion of a task to develop rotary signal-level transformers for the Galileo Spacecraft Project. The physical configuration of a rotary power transformer has a significant effect on its magnetic and electrical characteristics and therefore impacts the design of the dc/ac inverter driver. Important characteristics addressed during this development effort include: operating frequency, efficiency, transformer gap size, leakage inductance, and leakage flux. A breadboard inverter and rotary transformer were designed, fabricated and tested.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 4
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    Experimental and systems studies of the alkali metal thermoelectric converter for aerospace power (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 15, p. 2361, Accession no. A82-31876
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Energy (ISSN 0146-0412); 7; 442-448
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  • 5
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    Liquid fluorine/hydrazine rhenium thruster update (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The status of a fluorine/hydrazine thruster development program is discussed. A solid rhenium metal sea-level thrust chamber was successfully fabricated and tested for a total run duration of 1075 s with 17 starts. Rhenium fabrication methods are discussed. A test program was conducted to evaluate performance and chamber cooling. Acceptable performance was reached and cooling was adequate. A flight-type injector was fabricated that achieved an average extrapolated performance value of 3608 N-s/kg (368 lbf-s/lbm). Altitude thrust chambers were fabricated. One chamber incorporates a rhenium combustor and nozzle with an area ratio of 15:1, and a columbium nozzle extension with area ratios from 15:1 to 60:1. The other chamber was fabricated completely with a carbon/carbon composite. Because of the attributes of rhenium for use in high-temperature applications, a program to provide the materials and processes technology needed to reliably fabricate and/or repair vapor-deposited rhenium parts of relatively large size and complex shape is recommended.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: APL The 1983 JANNAF Propulsion Meeting, Vol. 1; p 85-90
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  • 6
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    Automation concepts for large space power systems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A study was undertaken to develop a methodology for analyzing, selecting, and implementing automation functions for multi-hundred-kW photovoltaic power systems intended for manned space station. The study involved identification of generic power system elements and their potential faults, definition of automation functions and their resulting benefits, and partitioning of automation functions between power subsystem, central spacecraft computer, and ground. Automation to a varying degree was concluded to be mandatory to meet the design and operational requirements of the space station. The key drivers are indefinite lifetime, modular growth, high performance flexibility, a need to accommodate different electrical user load equipment, on-orbit assembly/maintenance/servicing, and potentially large number of power subsystem components. Functions that are good candidates for automation via expert system approach includes battery management and electrical consumables management.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 7
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    Computer memory power control for the Galileo spacecraft (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The developmental history, major design drives, and final topology of the computer memory power system on the Galileo spacecraft are described. A unique method of generating memory backup power directly from the fault current drawn during a spacecraft power overload or fault condition allows this system to provide continuous memory power. This concept provides a unique solution to the problem of volatile memory loss without the use of a battery of other large energy storage elements usually associated with uninterrupted power supply designs.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 8
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    Preliminary comparison of laser and solar space power systems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Four laser receiver systems are compared to onboard solar photovoltaic power generation for spacecraft electrical requirements. The laser photovoltaic and laser MHD receivers were found to be lighter than a comparable planar solar photovoltaic system. The laser receiver also shows less drag at lower altitudes. Panel area is also reduced for the laser receiver allowing fewer Shuttle trips for construction. Finally, it is shown that a 1 megawatt laser and receiver system might be constructed with less weight than a comparable planar solar photovoltaic system.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 9
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    Computing the projected area of a spacecraft solar array with matrices (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Matrix methods for computing the projected area of a solar array as a function of the rotational position of a spacecraft and of array position on a spacecraft are presented. Formulas are derived which provide the optimum solar array pitch, cant and tracking angles for a given spacecraft configuration and orbit. These formulas are general and applicable to many spacecraft. Formulas are also provided for determining the energy output from an array for a given orbit and the resultant energy available to spacecraft loads. Results are simply obtained and realizable with a hand calculator. The methods above can be extended to the case of computer analysis of solar array shadowing. How this can be done is outlined and results are presented from a spacecraft study program.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 10
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    High voltage battery cell scanner development (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Battery cell voltage scanners have been previously used in low voltage spacecraft applications. In connection with future missions involving an employment of high-power high voltage power subsystems and/or autonomous power subsystem management for unattended operation, it will be necessary to utilize battery cell voltage scanners to provide battery cell voltage information for early detection of impending battery cell degradation/failures. In preparation for such missions, a novel battery cell voltage scanner design has been developed. The novel design makes use of low voltage circuit modules which can be applied to high voltage batteries in a building block fashion. A description is presented of the design concept and test results of the high voltage battery cell scanner, and its operation with an autonomously managed power subsystem is discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 11
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    Evidence of erosive burning in shuttle solid rocket motor (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Known models of Shuttle Solid Rocket Motor (SRM) performance have failed to produce pressure-time traces which accurately matched actual motor performance, especially during the first 5 seconds after ignition and during the last quarter of web burn time. Efforts to compensate for these differences in model reconstruction and actual performance resulted in resorting to the use of a Burning Anomaly Rate Function (BARF). It was suspected that propellant erosive burning was primarily responsible for the variation of model from actual results. The three dimensional Hercules Grain Design and Internal Ballistics Evaluation Program was made operational and slightly modified and an extensive trial and error effort was begun to test the hypothesis of erosive burning as an explanation of the burning anomaly. It was found that introduction of erosive burning (using Green's erosive burning equation) over portions of the aft segment grain and above a threshold gas Mach number did, in fact, give excellent agreement with the actual motor trace.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: APL The 1983 JANNAF Propulsion Meeting, Vol. 1; p 7-13
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  • 12
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    Detonation propulsion experiments and theory (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 17, p. 2705, Accession no. A82-35015
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: (ISSN 0001-1452)
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  • 13
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    Hydrocarbon rocket engines for earth-to-orbit vehicles (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 3280, Accession no. A81-40847
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: (ISSN 0022-4560)
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  • 14
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    Electric power - Looking at regenerative systems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Photovoltaic solar array technology dominates NASA space station planning for the late 1980s, although the reduction of fabrication costs and the extension of service life for such arrays remain essential goals for research and development. Attention is given to concentrator arrays, in which highly reflective surfaces concentrate solar energy onto the solar cells. Two types of concentrator arrays are under consideration: one with a low geometric concentration ratio which after reflector losses can produce about 5 suns at the cell surface, and the other with a Cassegrainian concentrator that produces a flux level of 100 suns on the cell surface. Costs are reduced from the $300/W for planar arrays to $250/W and as little as $100/W, respectively, in 1982 dollars. The storage of electrical energy by means of novel battery systems is also considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 21; Mar. 198
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  • 15
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    A study of some features of ac and dc electric power systems for a space station (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This study analyzes certain selected topics in rival dc and high frequency ac electric power systems for a Space Station. The interaction between the Space Station and the plasma environment is analyzed, leading to a limit on the voltage for the solar array and a potential problem with resonance coupling at high frequencies. Certain problems are pointed out in the concept of a rotary transformer, and further development work is indicated in connection with dc circuit switching, special design of a transmission conductor for the ac system, and electric motors. The question of electric shock hazards, particularly at high frequency, is also explored. and a problem with reduced skin resistance and therefore increased hazard with high frequency ac is pointed out. The study concludes with a comparison of the main advantages and disadvantages of the two rival systems, and it is suggested that the choice between the two should be made after further studies and development work are completed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson (Lyndon B.) Space Center The 1983 NASA/ASEE Summer Faculty Fellowship Research Program Research Reports; NASA. Johnson (Lynd
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  • 16
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    IPACS Guidance Navigation and Control System Considerations and Test Activities (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: The MSFC facility proposed for the Space Station Attitude Control Simulator which consists of a large three degree of freedom table driven by computer controlled hydraulic actuators designed to give high bandwidth and extremely fine control through large angles is outlined. The facility includes star and solar simulators providing collimated light with the spectral content and intensity typical of Earth orbit.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 165-168
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  • 17
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    Space Station Control Requirements and Flywheel System Weights for Combined Momentum and Energy Storage (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: The specifications of the flywheel system for momentum storage and vehicle torquing are somewhat dependent upon the attitude control requirements of the space station in orbit. As a ground rule, the flywheel system will be sized large enough to provide all attitude maneuvers, if practical, to avoid or minimize turning on the reaction control system (RCS). The RCS, whenever used, expels expensive mass and tends to contaminate optical surfaces of the vehicle. The vehicle rate and acceleration specifications of 0.10 deg/sec and 0.01 deg/square sec are tentative, and may be reduced if lesser values are more practical for flywheel design. For local vertical attitude hold, the average attitude error should be zero, and not the classical 1 degree, since control moment gyro (CMG) gimbal angles provide an exact reference feedback for gravity gradient momentum. Docking presents a problem for docking transients and attitude alignment which will require use of the RCS.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 77-92
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  • 18
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    Space Station Attitude Control System Concept and Requirements (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: There is currently no single Space Station configuration which is accepted as a baseline. However, the latest approach is toward symmetry in both geometry and mass distribution. This minimizes aerodynamic and gravity gradient torques. Solar arrays and radiators drive the configuration strongly. One axis of the solar arrays needs to be perpendicular to the orbit plane, and the geometric and principal axis should remain common along this axis to minimize secular torques. The need for both inertial and earth-fixed modes drives the structure of the Station toward a disk-like shape in the orbital plane.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 63-69
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  • 19
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    Combined Attitude Control and Energy Storage (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: The effect on attitude control by multiple wheels (used for energy storage) is described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 93-98
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  • 20
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    GSFC Flywheel Status (1983)
    In:  CASI
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    Publication Date: 2014-09-10
    Description: The assessment of flywheel energy storage for spacecraft power system is based on the conceptual flywheel design. This conceptual design of an integrated flywheel is based on the Mechanical Capacitor which evolved from development of magnetic bearings and permanent magnet ironless-brushless DC motors. The mechanical capacitor is based on three key technologies: (1) a composite rotor with a low ID to OD ratio for high energy density (weight and volume); (2) magnetic suspension close to the geometric center of the rotating mass to minimize loads normally encountered on the ends of a shaft, a no-wear mechanism in a vacuum environment, and to minimize losses at high rotational speeds; (3) permanent magnet ironless-brushless DC motor/generator for high efficiency of conversion and low losses at high rotational speeds. The complete system would include the necessary electronics for the motor/generator, containment, and counterrotating wheels for attitude control compatibility.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 23-34
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  • 21
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    IPACS Attitude Control Technology Considerations (1983)
    In:  CASI
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    Publication Date: 2014-09-10
    Description: Larger facilities or the Space Station and its evolutionary versions are considered for the control bandwidth which will evolve to lower values, probably in the 0.01 to 0.1 hertz range. An integrated power attitude control systems (IPACS) unit that incorporates conventional mechanical bearings to have a bandwidth of 4-10 hertz is expected. If the IPACS unit incorporates the advanced technology magnetic bearing, a bandwidth of 1.2 hertz is expected. It is found that for the Space Station or even the Space Platform, either of the above IPACS concepts are adequate.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 99-104
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  • 22
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    Electrical Power Trade-Offs (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: Electrical power trade studies were initiated in September 1982 supporting the Space Station Systems Definition activity. Responsibility for performing the electrical power trade studies (Power Data Base) was divided between the NASA Centers. Center representatives and their respective subjects are identified in the accompanying chart. The data base material was used to conduct a general storage trade study. When the results appeared to favor the flywheel option, effort was focused on a comparative flywheel investigation wherein a range of flywheel performance and cost possibilities was compared with optimistic projections of competing options.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 49-56
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  • 23
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    Overview of State-Of-The-Art Flywheel Technology (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: The technology and applications evaluation task focuses on defining performance and cost requirements for flywheels in the various areas of application. To date the DOE program has focused on automotive applications. The composite materials effort entails the testing of new commercial composites to determine their engineering properties. The rotor and containment development work uses data from these program elements to design and fabricate flywheels. The flywheels are then tested and their performance is evaluated to indicate possible areas for improvement. Once a rotor was fully developed it is transferred to the private sector.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 35-46
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  • 24
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    Power System Considerations and Test Activities (1983)
    In:  CASI
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    Publication Date: 2014-09-11
    Description: The potential benefits of an IPACS system compared to NiCd and/or Regen Fuel Cell systems are summarized. The benefits are: (1) significant life cycle cost savings; (2) total weight to orbit savings (30 yrs) as much as 10 times; (3) end to end efficiency increase results in approximately 10 kW reduction in array size(6%); (4) motor/generator controller regulation during discharge simplifies distribution system; and (5) momentum stored for attitude control increased by 4 times.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 157-164
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  • 25
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    Assessment of Potential for Batteries in Space Applications (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-11
    Description: Different battery technologies for energy storage in space missions were examined. One of the best ways of the possibilities of high energy density batteries were determined by looking at more conventional batteries (i.e., lead-acid, nickel-cadmium, nickel-hydrogen, etc.). The theoretical specific energy density for state of the art batteries and the usable energy density for a reasonable life expectancy are outlined. The most mature of these couples is lead acid, which achieves nearly 20% of its theoretical capacity. The nickel-cadmium couple, has matured to where the active capacity is 17% of its theoretical capacity. The achievements are used to measure the practicality of more advanced batteries and to estimate what is needed for future high power space systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 171-174
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  • 26
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    Advanced Control and Power System (ACAPS) Technology Program (1983)
    In:  CASI
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    Publication Date: 2014-09-11
    Description: The advanced control and power system (ACAPS) program is to establish the technology necessary to satisfy space station and related large space structures requirements for efficient, reliable, and cost effective energy storage and attitude control. Technology advances in the area of integrated flywheel systems capable of performing the dual functions of energy storage and attitude control are outlined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Integrated Flywheel Technol., 1983; p 141-156
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  • 27
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    Flywheel Electronics (1983)
    In:  CASI
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    Publication Date: 2014-09-11
    Description: Requirements of the flywheel electronic system are to accelerate the momentum wheel to a fixed maximum speed when solar energy is available and to maintain a constant voltage on the spacecraft bus under varying loads when solar energy is not available. Requirements, energy flow control, types of motors considered, type of electronic control, and efficiency considerations, are outlined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 105-116
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  • 28
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    The Boeing Flywheel Study (1983)
    In:  CASI
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    Publication Date: 2014-09-11
    Description: The major features of the history of the Boeing flywheel were studied. The analysis of the regenerative fuel cell was started as an outgrowth of the original Boeing study of the Space Operations Center, and was completed in November 1982 with the publication of the final report number D180-27160-1. The current flywheel effort attempts to study the integrated flywheel using the same ground rules that were used on the fuel cell study.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 71-76
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  • 29
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    Annular Momentum Control Device (AMCD) (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: The Annular Momentum Control Device (AMCD) concept, applications, and advantages as a momentum storage device are discussed. A laboratory test model AMCD was designed and built. The laboratory model AMCD is described and the results of the laboratory model test phase are presented. The efforts required to complete the AMCD laboratory model test phase are outlined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Integrated Flywheel Technol., 1983; p 123-132
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  • 30
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    Magnetic Bearings for Inertial Energy Storage (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: The selection of a noncontacting bearing technique with no wear out phenomena and which is vacuum compatible which is the decisive factor in selecting magnetic bearings for kinetic energy storage was investigated. Unlimited cycle life without degradation is a primary goal. Storage efficiency is a key parameter which is defined as the ratio of the energy remaining to energy stored after a fixed time interval at no load conditions. Magnetic bearings, although noncontacting, are not perfectly frictionless in that magnetic losses due to eddy currents and hysteresis can occur. Practical magnetic bearings, however, deviate from perfect symmetry and have discontinuities and asymmetric flux paths either by design or when controlled in the presence of disturbances, which cause losses. These losses can be kept smaller in the bearings than in a high power motor/generator, however, are a significant factor in selecting the magnetic bearing type.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 133-140
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  • 31
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    Space Station Energy Sizing (1983)
    In:  CASI
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    Publication Date: 2014-09-10
    Description: A general schematic for a space station power system is described. The major items of interest in the power system are the solar array, transfer devices, energy storage, and conversion equipment. Each item will have losses associated with it and must be utilized in any sizing study, and can be used as a checklist for itemizing the various system components.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 57-62
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  • 32
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    IPACS Electronics: Comments on the Original Design and Current Efforts at Langley Research Center (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: The development of the integrated power altitude control system (IPACS) is described. The power bridge was fabricated, and all major parts are in hand. The bridge was tested with a 1/4 HP motor for another program. The PWM, Control Logic, and upper bridge driver power supply are breadboarded and are debugged prior to starting testing on a passive load. The Hall sensor circuit for detecting rotor position is in design.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Integrated Flywheel Technol., 1983; p 117-122
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  • 33
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    Propulsion and fluid management - Station keeping will eat energy on a new scale (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: An attempt is made to identify technologies that could be brought to a state of minimal development risk in the near term, yet offer the potential for evolutionary growth consistent with future space station propulsion requirements. Prospective auxiliary propulsion propellants will be usable by other systems, thereby offering resupply benefits and a benign rather than corrosive or toxic handling environment. NASA programs are currently underway to develop the storage and supply methods for cryogenic liquids in orbit. The recovery of unused propellants from the Space Shuttle Orbiter and External Tank are being evaluated in order to define Shuttle modifications and performance penalties. Fluid management subsystem requirements and characteristics cannot, however, be fully defined until a firm mission scenario has been established and other space station subsystems are more clearly defined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 21; Mar. 198
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  • 34
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    Prediction of a propellant tank pressure history using state space methods (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An analysis of the time response of a propellant supply system operating in the blowdown mode is presented. The supply system is part of a pump-fed propulsion system intended for use on interplanetary spacecraft. As such, the supply system must provide the pump with propellant at sufficient pressure to avoid pump cavitation. The system, consisting of the tank, the liquid propellant, the pressurant gas and propellant vapor mixture, and a film layer separating the liquid and vapor phases, is analyzed using the principles of mass and energy conservation. The resulting set of ordinary, coupled, nonlinear differential equations for the thermodynamic state variables is integrated as an initial value problem. The resulting histories of total pressure, propellant vapor pressure, propellant liquid temperature, film layer temperature, propellant vapor/pressurant gas temperature, propellant vapor mass, and propellant liquid mass enable the calculation of the net positive suction head available at the pump which determines the viability of the pump-fed system concept when operated in the blowdown mode.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets; 20; Jan
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  • 35
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    Energy conversion for megawatt space power systems (1983)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Large nuclear space power systems capable of continuously producing over one megawatt of electrical power for a several year period will be needed in the future. This paper presents the results of a study to compare applicable conversion technologies which were deemed to be ready for a time period of 1995 and beyond. A total of six different conversion technologies were studied in detail and compared on the basis of conversion efficiency, radiator area, overall system mass, and feasibility. Three static, modular conversion technologies were considered; these include: AMTEC, thermionic, and thermoelectric conversion. The other three conversion technologies are heat engines which involve dynamic components. The dynamic systems analyzed were Brayton, Rankine, and the free piston Stirling engine. Each of the conversion techniques was also examined for limiting characteristics and an attempt was made to identify common research needs and enabling technologies.
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  • 36
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    Integrated Power/Attitude Control System (IPACS) (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: During orbit day, solar energy collected by the solar cell arrays and transformed into electrical energy is used to power the spacecraft subsystems, including the control system. In conventional spacecraft designs, a portion of the energy collected during the light portion of the orbit is stored in a set of batteries for use during orbit night. In the Integrated Power/Attitude Control System (IPACS) approach, that energy is stored in the rotating flywheel in the form of kinetic energy. Umbra electrical power demands are satisfied by attaching a generator to the wheel shaft and despinning the rotor. Through this approach, the battery system is no longer required and thus is eliminated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 5-21
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  • 37
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    Some Comments on Longevity by a Technologist (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-10
    Description: The durability of flywheels was investigated. Since only composite flywheels possess the potential for system energy densities in the range of 20 to 40 W hr/kg, and they are not yet at a level of maturity where a comfortable data base exists, the longevity aspects of the yet to be developed devices is still a speculation. The general methodologies that have been used in some of the more established technology areas to establish some degree of credibility in the ability to predict the upper limits of expected useful life based on the current limiting decay mechanism are outlined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center Integrated Flywheel Technol., 1983; p 175-185
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  • 38
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    Space Shuttle main engine powerhead structural modeling, stress and fatigue life analysis. Volume 2: Dynamics of blades and nozzles SSME HPFTP and HPOTP (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Normal modes of the blades and nozzles of the HPFTP and HPOTP are defined and potential driving forces for the blades are identified. The computer models used in blade analyses are described, with results. Similar information is given for the nozzles.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171000 , NAS 1.26:171000 , LMSC-HREC-TR-D867333-II
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  • 39
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    SSME structural dynamic model development (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A mathematical model of the Space Shuttle Main Engine (SSME) as a complete assembly, with detailed emphasis on LOX and High Fuel Turbopumps is developed. The advantages of both complete engine dynamics, and high fidelity modeling are incorporated. Development of this model, some results, and projected applications are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170960 , NAS 1.26:170960 , LMSC-HREC-TR-D867307
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  • 40
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    Feasibility demonstration of booster cross-over system for 3 1/2 inch SRB/MLP frangible nut system (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recent testing of the SRB/MLP Frangible Nut System (SOS Part Number 114850-9/Boosters P/N 114848-3) at NASA indicated a need to reduce the function time between boosters (2) within a single frangible nut. These boosters are initiated separately by electrical impulse(s). Coupling the output of each detonator with an explosive cross-over would reduce the function time between boosters (independent of electrical impulse) while providing additional redundancy to the system. The objectives of this program were to: provide an explosive cross-over between boosters, reduce function time between boosters to less than one (1) millisecond within a given nut, reduce cost of boosters, be compatible with the existing frangible nut system, and meet requirements of USBI Spec's (nut 10SPC-0030, booster 10SPC-0031).
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170895 , NAS 1.26:170895 , TP-8877
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  • 41
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    Simplified power processing for ion-thruster subsystems (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Compared to chemical propulsion, ion propulsion offers distinct payload-mass increases for many future low-thrust earth-orbital and deep-space missions. Despite this advantage, the high initial cost and complexity of ion-propulsion subsystems reduce their attractiveness for most present and near-term spacecraft missions. Investigations have, therefore, been conducted with the objective to attempt to simplify the power-processing unit (PPU), which is the single most complex and expensive component in the thruster subsystem. The present investigation is concerned with a program to simplify the design of the PPU employed in a 8-cm mercury-ion-thruster subsystem. In this program a dramatic simplification in the design of the PPU could be achieved, while retaining essential thruster control and subsystem operational flexibility.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 42
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    Simplified power processing for ion-thruster subsystems (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A review of the thruster/power-processor-interface requirements for (mercury and inert gas) ion-thrusters, an evaluation of various approaches to simplifying the power-processor circuitry, and the test results of the recently developed 8-cm mercury-ion-thruster simplified power-processor unit (SPPU) are presented. The SPPU demonstrates the feasibility of stable thruster operation using highly simplified power-processing techniques and achieves an approximately tenfold reduction in the electronic parts count when compared to the existing power-processor unit (PPU) used in the Hughes/NASA Lewis Research Center 8-cm-diameter (mercury) Ion Auxiliary Propulsion Subsystem (IAPS).
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1394
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  • 43
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    Hydrazine gas generator performance on Space Shuttle (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The design, functions, performance, and applications of the hydrazine gas generators (GG) on the STS are detailed. The GGs provide gas horse power for the APUs that drive the hydraulic pumps on the SRBs, which have two cross-linked systems. The Orbiter has three-cross-linked APU systems, used for gimballing the main engine and booster nozzles, actuating the main engine fuel valves and the ET umbilical disconnect, actuation of the control surfaces, and powering the landing gear, brakes, and nose wheel steering. The major design components of the Orbiter GGs are an injector, a catalyst bed, a decomposition chamber, an exhaust nozzle, and an interface structure, with the main structural material being Hasteloy B. Hydrazine injected and dispersed into the catalyst bed decomposes into gas and exits for expansion in an APU turbine. Twenty-six GGs have flown on missions STS-1 through STS-6 with over three tons of hydrazine having been expended over 44 hr of operations, as no refurbishment to that point was necessary.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1381
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  • 44
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    Vapor flow into a capillary propellant-acquisition device (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: An analytical model is described that specifies the conditions needed to cause a flow of vapor through the screens of a start basket. The analytical model is composed of several original submodels that interrelate the evaporation of the liquid in the basket, the bubble-point change of a screen in the presence of wicking, the drying out of a screen through a combination of evaporation and pressure difference, the vapor flow rate across a wet screen as a function of pressure difference, and the effect on wicking of a difference between the static pressure of the liquid reservoir and the vapor surrounding the screen. Most of the interrelations were demonstrated by a series of separate-effects tests, which were also used to determine certain empirical constants. The equations of the model were solved numerically for typical start basket designs. A simplified start basket was constructed and tested to verify these predictions, using both volatile and non-volatile liquids. The test results verified the trends predicted by the model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1380
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  • 45
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    LO2/LH2 propulsion for outer planet orbiter spacecraft (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Galileo class orbiter missions (750-1500 kg) to the outer planets require a large postinjection delta-V for improved propulsion performance. The present investigation shows that a pump-fed low thrust LO2/LH2 propulsion system can provide a significantly larger net on-orbit mass for a given delta-V than a state-of-the-art earth storable, N2O4/monomethylhydrazine pressure-fed propulsion system. A description is given of a conceptual design for a LO2/LH2 pump-fed propulsion system developed for a Galileo class mission to the outer planets. Attention is given to spacecraft configuration, details regarding the propulsion system, the thermal control of the cryogenic propellants, and aspects of mission performance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1305
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  • 46
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    Advanced LOX/H2 engine technologies for future OTVs (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: It is pointed out that NASA and DOD missions of the near future include, by current estimates, approximately 50 highly energetic missions to geosynchronous orbit. Advanced concepts make use of the Space Shuttle to transport the assembled orbital transfer vehicle (OTV) to low earth orbit (LEO) or to bring components and propellants from which to assemble the OTV in LEO. An advanced expander cycle engine based upon the RS-44 engine design has been planned for ultimate use with advanced space-based OTVs. Its design features complement the characteristics of manned space-based aeroassist vehicles which will provide the most cost-effective means for payload transfer between LEO and GEO orbits. A test-bed program is planned for early demonstration of the advanced expander cycle engine operation.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1312
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  • 47
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    A parametric study of thermally augmented O2/H2 rocket enines (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: An analysis is presented of the performance of a conceptual propulsion system in which liquid hydrogen and liquid oxygen are first vaporized and heated by thermal power from a spacecraft nuclear electric power supply prior to combustion in a rocket engine. Calculations of the specific impulse (I-sp) are presented for a series of O2/H2 oxidizer-to-fuel mixture ratios and reactant pre-heat temperatures (T-aug). It is found that the ratio of the augmentation power to the total engine jet power (P-aug/P-tot) determines the engine thrust for a given P-aug, T-aug, and I-sp. In addition, the performance of an unaugmented O2/H2 and a heated-hydrogen rocket engine were also calculated for the same conditions. Results show that an augmented O2/H2 engine has three to eight times the thrust of a heated H2 engine for a given P-aug. It is concluded that it should be possible to design a high/low thrust propulsion system using a common propellant, with the option of using thermal power from the nuclear electric power supply to augment the low-thrust propulsion system during cruise periods when the reactor's full electric power is not needed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1258
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  • 48
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    Radiation energy receiver for laser and solar propulsion systems (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The concept of remotely heating a rocket propellant with a high intensity radiant energy flux is especially attractive due to its high specific impulse and large payload mass capabilities. In this paper, a radiation receiver-thruster which is especially suited to the particular thermodynamic and spectral characteristics of highly concentrated solar energy is proposed. In this receiver, radiant energy is volumetrically absorbed within a hydrogen gas seeded with alkali metal vapors. The alkali atoms and molecules absorb the radiant flux and, subsequently, transfer their internal excitation to hydrogen molecules through collisional quenching. It is shown that such a radiation receiver would outperform a blackbody cavity type receiver in both efficiency and maximum operating temperatures. A solar rocket equipped with such a receiver-thruster would deliver thrusts of several hundred newtons at a specific impulse of 1000 seconds.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1207
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  • 49
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    Effects of tripropellant engines on earth-to-orbit vehicles (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effects of tripropellant engines on earth-to-orbit vehicles is examined in terms of their impact on engine configurations and launch capabilities. Hydrocarbon fuel with some oxygen is used in tripropellant fuels, with hydrogen as a back-up fluid for coolant and driving the pumps. Engine concepts which implement tripropellant fuels include a hydrogen-gas generator engine with staged combustion, a two-mode engine burning hydrocarbon fuel in one chamber and hydrogen in another, a dual expander engine with a central hydrocarbon nozzle and an annular hydrogen nozzle, and a dual throat engine. The use of hydrocarbons reduces the fuel weight by providing a higher specific impulse than with LOX-LH2 systems alone. Studies have shown that single-stage-to-orbit vehicles capable of lifting 13.6 Mg are possible with tripropellant engines. A dual-expander engine, is identified as offering the most fuel dry mass reduction for a given payload if cooling requirements can be satisfied. Further development of the tripropellant engines is concluded to be beneficial.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1187
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  • 50
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    Improvements in rocket engine nozzle and high altitude plume computations (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The characteristics of rocket exhaust flow fields are very complex, and many phenomena are involved. Previously, it was necessary to use a multitude of codes to treat a nozzle/plume flow in detail. In connection with both computational and economic standpoints, however, it is desirable to have a single code which can treat all the dominant phenomena in a rocket nozzle/plume flow field. The present investigation has the objective to describe a nozzle plume flowfield code which has capabilities that do not presently exist in a single computer code. The RAMP code considered by Penny et al. (1976) was used as a basis in the development of the new code. The basic RAMP employs modular construction and provides a two-phase, reacting gas, supersonic inviscid nozzle/plume solution. Other capabilities needed, which in most cases already exist in other computer codes, were incorporated into the RAMP code to enhance its usefulness. Attention is given to results of plume calculations for bipropellant and solid propellant motors.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1547
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  • 51
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    A reexamination of the laser supported combustion wave (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Kantrowitz (1972) and Minovitch (1972) have proposed the use of laser sustained plasmas as a means to heat a rocket propellant. Recent studies of laser-powered propulsion have been directed toward the application of high-specific-impulse space propulsion systems for orbital transfer missions. Analyses of rocket performance relied heavily on the concept of the laser-supported combustion (LSC) wave. Raizer (1971) first drew the analogy between laser-sustained plasmas and combustion waves in an analysis. The Raizer model was later applied to hydrogen by Kemp and Root (1979). In connection with certain problems arising with the approach considered by Kemp and Root, the present investigation is concerned with a reexamination of the Raizer model. Attention is given to a numerical approach for the entire LSC wave in hydrogen, taking into account the incorporation of the proper boundary conditions far downstream of the wave.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1444
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  • 52
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    Measured performance of a multimegawatt MPD thruster (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Previously cited in issue 12, p. 1960, Accession no. A81-29538
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: (ISSN 0022-4560)
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  • 53
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    Characterization of advanced electric propulsion systems (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Previously cited in issue 17, p. 2707, Accession no. A82-35083
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: (ISSN 0022-4560)
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  • 54
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    An inviscid three-dimensional analysis of the Space Shuttle main engine hot-gas manifold (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A numerical study using an inviscid three-dimensional Lagrangian fluid dynamics code has been conducted as a part of an overall effort to understand the flow behavior in the SSME fuel side hot-gas manifold. The model simulates flow from the high-pressure fuel turbine exit through the transfer ducts, including the effects of swirl, inlet flow symmetry, and presence of straightening vanes and struts; a separate, more-detailed effort is in progress that includes viscosity and turbulence effects. The simplified model presented is divided into two parts, the first includes the 180-degree turnaround duct downstream of the turbine exit and the spherical fuel bowl section, while the second models the three transfer ducts. The two parts of the model are coupled together with the interface conditions being updated through iteration. Results indicate that a transverse pressure differential of 165 psi would be imposed on the turbine exit and that unstable flow separation occurs around the vanes, struts, and within the transfer ducts. The three transfer ducts show a mass flux split of approximately 41, 21, and 38 percent. Results to date are encouraging that certain flow characteristics can be usefuly represented using a relatively coarse grid inviscid code.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1523
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  • 55
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    Development of a simplified procedure for rocket engine thrust chamber life prediction with creep (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analytical method for predicting engine thrust chamber life is developed. The method accounts for high pressure differentials and time-dependent creep effects both of which are significant in limiting the useful life of the shuttle main engine thrust chamber. The hot-gas-wall ligaments connecting adjacent cooling channels ribs and separating the coolant flow from the combustion gas are subjected to a high pressure induced primary stress superimposed on an alternating cyclic thermal strain field. The pressure load combined with strain-controlled cycling produces creep ratcheting and consequent bulging and thinning of these ligaments. This mechanism of creep-enhanced ratcheting is analyzed for determining the hot-gas-wall deformation and accumulated strain. Results are confirmed by inelastic finite element analysis. Fatigue and creep rupture damage as well as plastic tensile instability are evaluated as potential failure modes. It is demonstrated for the NARloy Z cases analyzed that when pressure differentials across the ligament are high, creep rupture damage is often the primary failure mode for the cycle times considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168261 , NAS 1.26:168261 , ODAI-1512-11-83
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  • 56
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    Sputtering phenomena in ion thrusters (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Sputtering effects in discharge chambers of ion thrusters are lifetime limiting in basically two ways: (1) ion bombardment of critical thruster components at energies sufficient to cause sputtering removes significant quantities of material; enough to degrade operation through adverse dimensional changes or possibly lead to complete component failure, and (2) metals sputtered from these intensely bombarded components are deposited in other locations as thin films and subsequently flake or peel off; the flakes then lodge elsewhere in the discharge chamber with the possibility of providing conductive paths for short circuiting of thruster components such as the ion optics. This experimental work has concentrated in two areas. The first has been to operate thrusters for multi-hour periods and to observe and measure the films found inside the thruster. The second was to simulate the environment inside the discharge chamber of the thruster by means of a dual ion beam system. Here, films were sputter deposited in the presence of a second low energy bombarding beam to simulate film deposition on thruster interior surfaces that undergo simultaneous sputtering and deposition. Mo presents serious problems for use in a thruster as far as film deposition is concerned. Mo films were found to be in high stress, making them more likely to peel and flake.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168172 , NAS 1.26:168172
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  • 57
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    Study of auxiliary propulsion requirements for large space systems, volume 2 (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A range of single shuttle launched large space systems were identified and characterized including a NASTRAN and loading dynamics analysis. The disturbance environment, characterization of thrust level and APS mass requirements, and a study of APS/LSS interactions were analyzed. State-of-the-art capabilities for chemical and ion propulsion were compared with the generated propulsion requirements to assess the state-of-the-art limitations and benefits of enhancing current technology.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168193-VOL-2 , NAS 1.26:168193-VOL-2 , D180-27728-2
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  • 58
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    Improved Two-Dimensional Kinetics (TDK) computer program (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Fluid properties, the boundary layer module, and regenerative cooling are discussed. Chemistry, low density flow effects, test cases, input and output for TDK, and documentation are also discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170922 , NAS 1.26:170922 , SN-54
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  • 59
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    Investigation of a pulsed electrothermal thruster (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Exhaust velocity and thrust measurements are performed on a pulsed electrothermal thruster using polyethylene and Teflon propellants. The results verify theoretical predictions of equilibrium flow in the nozzle, resulting in substantial recovery of the energy of dissociation and ionization. The thruster is tested in an unsteady mode (15 micro sec current pulse and 15 cm discharge length) and in a quasi-steady mode (48 micro sec current pulse and 5 cm discharge length). All tests are run at 2 kJ. The exhaust velocity of the propellant mass exiting during the current pulse is measured with two types of time of flight probes, and the impulse bit is measured on a thrust stand. It is inferred from both theory and experiment that an additional amount of mass is exhausted after the pulse. The measured thrust to power ratio for polyethylene is T/P = 0.10 NkW at 21 km/sec in the unsteady mode, and T/P = .053 N/kW at 27 km/sec in the quasi-steady mode, where the velocities are measured by the time-of-flight probes. For Teflon propellant, T/P = .20 N/kW at 15 km/sec (unsteady mode) and 0.090 N/kW at 20 km/sec (quasi-steady mode). The discharge pressure and temperature predicted by a computational model for polyethylene are consistent with the measured thrust and discharge resistance.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168266 , NAS 1.26:168266 , GTD-83-10
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  • 60
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    Study of auxiliary propulsion requirements for large space systems. Volume 1: Executive summary (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An insight into auxiliary propulsion systems (APS) requirements for large space systems (LSS) launchable by a single shuttle is presented. In an effort to scope the APS requirements for LSS, a set of generic LSSs were defined. For each generic LSS class a specific structural configuration, representative of that most likely to serve the needs of the 1980's and 1990's was defined. The environmental disturbance forces and torques which would be acting on each specific structural configuration in LEO and GEO orbits were then determined. Auxiliary propulsion requirements were determined as a function of: generic class specific configuration, size and openness of structure, orbit, angle of orientation, correction frequency, duty cycle, number and location of thrusters and direction of thrusters and APS/LSS interactions. The results of this analysis were used to define the APS characteristics of: (1) number and distribution of thrusters, (2) thruster modulation, (3) thrust level, (4) mission energy requirements, (5) total APS mass component breakdown, and (6) state of the art adequacy/deficiency.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168193-VOL-1 , NAS 1.26:168193-VOL-1 , D180-27728-1
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    Solid rocket booster thrust vector control subsystem description (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Major Solid Rocket Booster-Thrust Vector Control (SRB-TVC) subsystem components and subcomponents used in the Space Transportation System (STS) are identified. Simplified schematics, detailed schematics, figures, photographs, and data are included to acquaint the reader with the operation, performance, and physical layout as well as the materials and instrumentation used.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-82546 , NAS 1.15:82546
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  • 62
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    Space Shuttle main engine powerhead structural modeling, stress and fatigue life analysis. Volume 3: Stress summay of blades and nozzles at FPL and 115 percent RPL loads. SSME HPFTP and HPOTP blades and nozzles (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Gasdynamic environments applied to the turbine blades and nozzles of the HPFTP and HPOTP were analyzed. Centrifugal loads were applied to blades to account for the pump rotation of FPL and 115 percent RPL. The computer models used in the blade analysis with results presented in the form of temperature and stress contour plots are described. Similar information is given for the nozzles.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171001 , NAS 1.26:171001 , LMSC-HREC-TR-D867333-III
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  • 63
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    Space Shuttle main engine, powerhead structural modeling, stress and fatigue life analysis. Volume 4: Summary of investigation of unscheduled events and special tasks (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Low pressure fuel turbopump turbine labyrinth send tip rubbing analysis, gas dynamic analysis, and HPFTP blade crack and blade impact are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171002 , NAS 1.26:171002 , LMSC-HREC-TR-D867333-IV
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  • 64
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    Space Shuttle main engine powerhead structural modeling, stress and fatigue life analysis. Volume 1: Gasdynamic environment of the SSME HPFTP and HPOTP turbines (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Gasdynamic analysis for the turbine blades and nozzle vanes, HPFTP turbine analysis, and HPOTP turbine analysis are provided.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170999 , NAS 1.26:170999 , LMSC-HREC-TR-D867333-I
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  • 65
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    The SRB nozzle erosion related flow analysis (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study was performed to define the solid rocket booster (SRB) nozzle throat flow field, and to investigate one possible mechanism for the severe erosion which occurred on a recent flight. The flow field in the vicinity of the eroded area was not found to be exceptional, and the presence of a notch or scored area near the imbedded region nose did not appear to produce sufficient flow fluctuations to exacerbate the erosion characteristics of the throat liner. An interesting fluctuating mechanism was found in the imbedded cavity, but that mechanism (while of possible importance for erosion of the seal region) did not seem to adversely affect the region of concern. On the basis of this analysis, the conclusion can be drawn that the anomalous erosion did not result from a single mechanical defect (pit, or gouge) since the flow fluctuations which result seem insufficient to induce a repetitive pattern downstream. It further appears that the emission pattern exhibited did not result from a steady flow phenomena in the throat region. This does not rule out acoustic phenomena or severe start-up transients.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170961 , NAS 1.26:170961
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  • 66
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    Development of advanced inert-gas ion thrusters (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Inert gas ion thruster technology offers the greatest potential for providing high specific impulse, low thrust, electric propulsion on large, Earth orbital spacecraft. The development of a thruster module that can be operated on xenon or argon propellant to produce 0.2 N of thrust at a specific impulse of 3000 sec with xenon propellant and at 6000 sec with argon propellant is described. The 30 cm diameter, laboratory model thruster is considered to be scalable to produce 0.5 N thrust. A high efficiency ring cusp discharge chamber was used to achieve an overall thruster efficiency of 77% with xenon propellant and 66% with argon propellant. Measurements were performed to identify ion production and loss processes and to define critical design criteria (at least on a preliminary basis).
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168206 , NAS 1.26:168206
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  • 67
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    Design, fabrication and testing of porous tungsten vaporizers for mercury ion thrusters (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The dispersions in the characteristics, performance and reliability of vaporizers for early model 30-cm thrusters were investigated. The purpose of the paper is to explore the findings and to discuss the approaches that were taken to reduce the observed dispersion and present the results of a program which validated those approaches. The information that is presented includes porous tungsten materials specifications, a discussion of assembly procedures, and a description of a test program which screens both material and fabrication processes. There are five appendices providing additional detail in the areas of vaporizer contamination, nitrogen flow testing, bubble testing, porosimeter testing, and mercury purity. Four neutralizers, seven cathodes and five main vaporizers were successfully fabricated, tested, and operated on thrusters. Performance data from those devices is presented and indicates extremely repeatable results from using the design and fabrication procedures.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-83063 , E-1534 , NAS 1.15:83063
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  • 68
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    Analysis and test for space shuttle propellant dynamics (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of a study to develop an analytical model capable of predicting the dynamic interaction forces on the Shuttle External Tank, due to large amplitude propellant slosh during RTLS separation. The report details low-g drop tower and KC-135 test programs that were conducted to investigate propellant reorientation during RTLS. In addition, the development of a nonlinear finite element slosh model (LAMPS2, two dimensional, and one LAMPS3, three dimensional) is presented. Correlation between the model and test data is presented as a verification of the modeling approach.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-3683 , NAS 1.26:3683 , MCR-81-528
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  • 69
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    Perfect bell nozzle parametric and optimization curves (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Nozzle contour data for untruncated Bell nozzles with expansion area ratios to 6100 and a specific heat ratio of 1.2 are provided. Curves for optimization of nozzles for maximum thrust coefficient within a given length, surface area, or area ratio are included. The nozzles are two dimensional axisymmetric and calculations were performed using the method of characteristics. Drag due to wall friction was included in the final thrust coefficient.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-RP-1104 , NAS 1.61:1104
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  • 70
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    Design considerations for large space electric power systems (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As power levels of spacecraft rise to the 50 to 100 kW range, it becomes apparent that low voltage (28 V) dc power distribution and management systems will not operate efficiently at these higher power levels. The concept of transforming a solar array voltage at 150 V dc into a 1000 V ac distribution system operating at 20 kHz is examined. The transformation is accomplished with series-resonant inverter by using a rotary transformer to isolate the solar array from the spacecraft. The power can then be distributed in any desired method such as three phase delta to delta. The distribution voltage can be easily transformed to any desired load voltage and operating frequency. The reasons for the voltage limitations on the solar array due to plasma interactions and the many advantages of a high voltage, high frequency at distribution system are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-83064 , E-1535 , NAS 1.15:83064
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  • 71
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    The electrothermal ramjet (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 17, p. 2707, Accession no. A82-35068
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 20; 603-610
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  • 72
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    Test verification of LOX/RP-1 high-pressure fuel/oxidizer-rich preburner designs (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 17, p. 2706, Accession no. A82-35032
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 20; 567-573
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  • 73
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    Test Report for MSFC Test No. 83-2: Pressure scaled water impact test of a 12.5 inch diameter model of the Space Shuttle solid rocket booster filament wound case and external TVC PCD (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Water impact tests using a 12.5 inch diameter model representing a 8.56 percent scale of the Space Shuttle Solid Rocket Booster configuration were conducted. The two primary objectives of this SRB scale model water impact test program were: 1. Obtain cavity collapse applied pressure distributions for the 8.56 percent rigid body scale model FWC pressure magnitudes as a function of full-scale initial impact conditions at vertical velocities from 65 to 85 ft/sec, horizontal velocities from 0 to 45 ft/sec, and angles from -10 to +10 degrees. 2. Obtain rigid body applied pressures on the TVC pod and aft skirt internal stiffener rings at initial impact and cavity collapse loading events. In addition, nozzle loads were measured. Full scale vertical velocities of 65 to 85 ft/sec, horizontal velocities of 0 to 45 ft/sec, and impact angles from -10 to +10 degrees simulated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170901 , NAS 1.26:170901 , TN-SM-83-12
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  • 74
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    Pulsed plasma thruster ignitor plug ignition characteristics (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 15, p. 2361, Accession no. A82-31913
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: (ISSN 0022-4560)
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  • 75
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    Advanced propulsion concepts for orbital transfer vehicles (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Studies of the United States Space Transportation System show that in the mid-to-late 1990s expanded capabilities for Orbital Transfer Vehicles (OTV) will be needed to meet increased payload requirements for transporting materials and possible men to geosynchronous orbit. NASA is conducting a technology program in support of an advanced propulsion system for future OTVs. This program is briefly described with results to date of the first program element, the Conceptual Design and Technology Definition studies. Previously announced in STAR as N83-26924
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1243
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  • 76
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    Auxiliary propulsion requirements for large space systems (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An insight into auxiliary propulsion systems (APS) requirements for large space systems (LSS) launchable by a single shuttle is presented. In an effort to scope the APS requirements for LSS, a set of generic LSSs were defined. For each generic LSS class a specific structural configuration, representative of that most likely to serve the needs of the 1980's and 1990's was defined. The environmental disturbance forces and torques which would be acting on each specific structural configuration in LEO and GEO orbits were then determined. Auxiliary propulsion requirements were determined as a function of: generic class specific configuration, size and openness of structure, orbit, angle of orientation, correction frequency, duty cycle, number and location of thrusters and direction of thrusters and APS/LSS interactions. The results of this analysis were used to define the APS characteristics of: (1) number and distribution of thrusters, (2) thruster modulation, (3) thrust level, (4) mission energy requirements, (5) total APS mass component breakdown, and (6) state of the art adequacy/deficiency. Previously announced in STAR as N83-26922
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1217
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  • 77
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    Advanced beamed-energy and field propulsion concepts (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Specific phenomena which might lead to major advances in payload, range and terminal velocity of very advanced vehicle propulsion are studied. The effort focuses heavily on advanced propulsion spinoffs enabled by current government-funded investigations in directed-energy technology: i.e., laser, microwave, and relativistic charged particle beams. Futuristic (post-year 2000) beamed-energy propulsion concepts which indicate exceptional promise are identified and analytically investigated. The concepts must be sufficiently developed to permit technical understanding of the physical processes involved, assessment of the enabling technologies, and evaluation of their merits over conventional systems. Propulsion concepts that can be used for manned and/or unmanned missions for purposes of solar system exploration, planetary landing, suborbital flight, transport to orbit, and escape are presented. Speculations are made on the chronology of milestones in beamed-energy propulsion development, such as in systems applications of defense, satellite orbit-raising, global aerospace transportation, and manned interplanetary carriers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-176108 , NAS 1.26:176108 , BDM/W-83-225-TR
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  • 78
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    Automated distribution system management for multichannel space power systems (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A NASA sponsored study of space power distribution system technology is in progress to develop an autonomously managed power system (AMPS) for large space power platforms. The multichannel, multikilowatt, utility-type power subsystem proposed presents new survivability requirements and increased subsystem complexity. The computer controls under development for the power management system must optimize the power subsystem performance and minimize the life cycle cost of the platform. A distribution system management philosophy has been formulated which incorporates these constraints. Its implementation using a TI9900 microprocessor and FORTH as the programming language is presented. The approach offers a novel solution to the perplexing problem of determining the optimal combination of loads which should be connected to each power channel for a versatile electrical distribution concept.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 79
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    The Galileo probe Li/SO2 battery (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: NASA's Galileo mission to Jupiter will consist of an orbiter and a probe, the probe to descend through and analyze the Jovian atmosphere. All power for the probe will be supplied by three battery modules containing a total of 39 D size Li/SO2 cells that will be required to retain capacity for the duration of the mission (over 50 months) and then provide current at 3 to 4 amperes for 48 minutes. The design, development, and testing of this battery are described herein.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 80
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    Optical, thermal, and electrical performance of low-CR solar arrays (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes the analysis and testing of a photovoltaic low-CR concentrator shaped like a truncated pyramid with an aperture of 0.5 m on a side and a geometric concentration ratio of six. The truncated base plane is covered by either silicon (Si) or gallium arsenide (GaAs) solar cells. Ray-trace analysis of the concentrator predicts a peak optical efficiency of 0.77, which falls off only gradually with pointing error. A coupled thermal-electrical analysis of the system shows that the moderately nonuniform illumination produced by the concentrator does not result in significant mismatch losses, provided the solar cells are connected in parallel groups. The results of ground tests involving a full-scale prototype concentrator conform well with theoretical predictions.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 81
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    Ion implanted junctions for silicon space solar cells (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper reviews the application of ion implantation to emitter and back surface field formation in silicon space solar cells. Experiments based on 2 ohm-cm boron-doped silicon are presented. It is shown that the implantation process is particularly compatible with formation of a high-quality back surface reflector. Large area solar cells with AM0 efficiency greater than 14 percent are reported.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 82
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    Energetic closed-cycle gas core reactors for orbit raising (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Closed-cycle gas core reactor power plants can be of two types. In the 'mixed flow' type, the gaseous nuclear fuel is intimately mixed with the working gas in the cavity. In the 'light bulb' type the fissioning plasma is enclosed in a transparent tube, and energy transfer to the separate working gas occurs by thermal radiation. The potentials of high temperature gas core reactors in terrestrial electric power generator applications have been considered, and a number of civilian power-beaming applications for gaseous fuel nuclear-MHD power plants in space have been suggested. Major conclusions of investigations related to the design of space power systems are discussed. Attention is given to options for conversion cycles, the power system specific mass, and research and technology issues.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 83
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    Algorithm development for a spacecraft autonomous power system (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Two algorithms were developed to demonstrate the implementation of autonomous functions in an existing spacecraft power system. The functions selected for autonomous operation include a typical performance monitoring function, battery state of charge, and a fault detection and response function represented by a battery state of charge below a preselected limit. The constraints imposed by the existing power system configuration are the available data in the telemetry stream and the existing commands and command structure. The areas requiring future development are the degree of battery characterization, the effects of hardware/software faults, and the verification of faults.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 84
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    Computer predictions of ground storage effects on performance of Galileo and ISPM generators (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Radioisotope Thermoelectric Generators (RTG) that will supply electrical power to the Galileo and International Solar Polar Mission (ISPM) spacecraft are exposed to several degradation mechanisms during the prolonged ground storage before launch. To assess the effect of storage on the RTG flight performance, a computer code has been developed which simulates all known degradation mechanisms that occur in an RTG during storage and flight. The modeling of these mechanisms and their impact on the RTG performance are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 85
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    Sublimation measurements and analysis of high temperature thermoelectric materials and devices (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: High temperature thermoelectric device sublimation effects are compared for rare earth sulfides, selenides, and state-of-the-art Si-Ge alloys. Although rare earth calcogenides can potentially exhibit superior sublimation characteristics, the state-of-the-art Si-Ge alloy with silicon nitride sublimation-inhibitive coating has been tested to 1000 C. Attention is given to the ceramic electrolyte cells, forming within electrical and thermal insulation, which affect leakage conductance measurements in Si-Ge thermoelectric generators.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 86
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    Tests of SSME low pressure pump in liquids at zero throughflow (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Shutdown requirements in space of the Space Shuttle Main Engines require that the low pressure pump operate under conditions of zero flow and zero NPSH and still be able to generate head and absorb torque. Ground tests were conducted in both water and liquid oxygen to verify these capabilities. The test facilities are described, and the test results are presented showing the pump performance at zero flow over a wide range of NPSH conditions including zero values. The influence of operating speed, fluid medium, and internal struts upstream of the inducer are presented. A flow model schematic is presented sketching a flow field in the pump that is consistent with the observed data.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 87
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    Development of the Space Shuttle main engine (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The history of the development, certification, and launch operations of the Space Shuttle Main Engine is described. Development problems and their solutions are discussed. Ground testing at both rated and full power levels involving four engines and eight certification test cycles totalling more than 40,000 seconds of hot-fire testing, which qualified both Columbia's and Challenger's engines for flight, are discussed. Ground checkout and flight performance of Columbia's and Challenger's engines are revealed. Future plans for the Space Shuttle Main Engine are outlined including flight certification testing to verify a life of 40 flights and 20,000 seconds operation before overhaul.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 83-386
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  • 88
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    Analysis of Full-Test tools and their limitations as applied to terminal junction blocks (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Discovery of unlocked contacts in Deutsch Block terminal junctions in Solid Rocket Booster flight hardware prompted an investigation into pull test techniques to help insure against possible failures. Internal frictional forces between socket and pin and between wire and grommet were examined. Pull test force must be greater than internal friction yet less than the crimp strength of the pin or socket. For this reason, a 100 percent accurate test is impossible. Test tools were evaluated. Available tools are adequate for pull testing.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-82520 , NAS 1.15:82520
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  • 89
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    CARS temperature measurements in the fuel preburner of the Space Shuttle main engine: A feasibility study (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report discusses the feasibility of making temperature profile measurements in the fuel preburner of the main engine of the space shuttle (SSME) using coherent anti-Stokes Raman spectroscopy (CARS). The principal thrust of the work is to identify problems associated with making CARS measurements in high temperature gas phase hydrogen at very high pressures (approx 400 atmospheres). To this end a theoretical study was made of the characteristics of the CAR spectra of H2 as a function of temperature and pressure and the accuracy with which temperatures can be extracted from this spectra. In addition the experimental problems associated with carrying out these measurements on a SSME at NSTL were identified. A conceptual design of a CARS system suitable for this work is included. Many of the results of the calculations made in this report are plotted as a function of temperature. In the course of presenting these results, it was necessary to decide whether the number of density or the pressure should be treated as a fixed parameter.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170764 , NAS 1.26:170764
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  • 90
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    High effectiveness liquid droplet/gas heat exchanger for space power applications (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A high-effectiveness liquid droplet/gas heat exchanger (LDHX) concept for thermal management in space is described. Heat is transferred by direct contact between fine droplets (approximately 100-300 microns in diameter) of a suitable low vapor pressure liquid and an inert working gas. Complete separation of the droplet and gas media in the zero-g environment is accomplished by configuring the LDHX as a vortex chamber.The large heat transfer area presented by the small droplets permits heat exchanger effectiveness of 0.9-0.95 in a compact, lightweight geometry which avoids many of the limitations of conventional plate and fin or tube and shell heat exchangers, such as their tendency toward single point failure. The application of the LDHX in a high temperature Brayton cycle is discussed to illustrate the performance and operational characteristics of this new heat exchanger concept.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 83-433
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  • 91
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    An engineering evaluation of the Space Shuttle OMS engine after 5 orbital flights (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Design features, performances on the first five flights, and condition of the Shuttle OMS engines are summarized. The engines were designed to provide a vacuum-fed 6000 lb of thrust and a 310 sec specific impulse, fueled by a combination of N2O4 and monomethylhydrazine (MMH) at a mixture ratio of 1.65. The design lifetime is 1000 starts and 15 hr of cumulative firing duration. The engine assembly is throat gimballed and features yaw actuators. No degradation of the hot components was observed during the first five flights, and the injector pattern maintained a uniform, enduring level of performance. An increase in the take-off loads have led to enhancing the wall thickness in the nozzle in affected areas. The engine is concluded to be performing to design specifications and is considered an operational system.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IAF PAPER 83-384
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    Acid droplet generation in SRM exhaust clouds (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A free energy analysis is applied to the co-condensation/evaporation of H2O and HCl vapors on wettable particles in open air in order to model droplet nucleation in solid rocket motor (SRM) exhaust clouds. Formulations are defined for the free energy change, the drop radius, the saturation ratio, the total number of molecules, and the mean molecular radius in solution, as well as the molecular volume and the concentration range. The free energy release in the phase transition for the AL2O3 nuclei in the SRM exhaust is examined as a function of the HCl molefraction and nucleating particle radius, based on Titan III launch exhaust cloud conditions 90 sec after ignition. The most efficient droplet growth is determined to occur at an HCl molefraction of 0.082 and a particle radius of 0.0000013 cm, i.e. a molality of 5.355.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-2615
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  • 93
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    Airborne measurements of Space Shuttle exhaust constituents (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Airborne measurements of hydrogen chloride (HCl) and particulates made during penetrations into and flights under Space Shuttle exhaust clouds from launches STS-1, -2, and -5 are presented to permit comparison with dispersion model predictions for Space Shuttle exhaust clouds, and with previous measurements made in Titan III exhaust clouds. Analytical techniques employed for the Shuttle measurements were developed and refined during earlier Titan III exhaust cloud measurements and include the measurements of particulate concentrations, size distributions, and the partitioning of HCl between the gaseous and aerosol phases. The results are useful in understanding the dynamics of ground cloud development, atmospheric dispersion, and potential environmental effects of Shuttle effluents.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-2587
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  • 94
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    A new approach to implementing spacecraft power system autonomy (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: Discussed in this paper are some of the problems associated with implementing microcomputer-based power system autonomy on spacecraft flight projects, as well as limitations derived from prior development programs. A new approach is given for developing the autonomy architecture, and an architecture concept, based on that approach, is described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-2419
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  • 95
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    Auxiliary propulsion requirements for large space systems (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An insight into auxiliary propulsion systems (APS) requirements for large space systems (LSS) launchable by a single shuttle is presented. In an effort to scope the APS requirements for LSS, a set of generic LSSs were defined. For each generic LSS class a specific structural configuration, representative of that most likely to serve the needs of the 1980's and 1990's was defined. The environmental disturbance forces and torques which would be acting on each specific structural configuration in LEO and GEO orbits were then determined. Auxiliary propulsion requirements were determined as a function of: generic class specific configuration, size and openness of structure, orbit, angle of orientation, correction frequency, duty cycle, number and location of thrusters and direction of thrusters and APS/LSS interactions. The results of this analysis were used to define the APS characteristics of: (1) number and distribution of thrusters, (2) thruster modulation, (3) thrust level, (4) mission energy requirements, (5) total APS mass component breakdown, and (6) state of the art adequacy/deficiency.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-TM-83388 , E-1666 , NAS 1.15:83388 , AIAA PAPER 83-1217 , Joint Propulsion Conf. and Tech. Display; Jun 27, 1983 - Jun 29, 1983; Seattle
    Format: application/pdf
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  • 96
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    The analysis and testing of blade platform friction dampers used in the high pressure fuel turbopump (HPFTP) of the Space Shuttle Main Engine (SSME) (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Premature cracking of the first stage turbine blades in HPFTP of the SSME could be alleviated by redesign of the platform friction dampers that are used to reduce the vibration response of the blades. Analytical studies by the lumped mass method of friction damper effectiveness and spin pit tests of a straingaged bladed disk have been performed. Methodologies used in the program are described. Preliminary results show that the effectiveness of the blade platform dampers can be increased if the frequency and amplitude of the most damaging forcing functions can be defined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Annual Mini-Symposium on Aerospace Science and Technology; Mar 22, 1983; Wright-Patterson AFB, OH
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  • 97
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    The 8-CM ion thruster characterization (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The performance capabilities of the 8 cm diameter mercury ion thruster were increased by modifying the thruster operating parameters and component hardware. The initial performance levels, representative of the Hughes/NASA Lewis Research Center Ion Auxiliary Propulsion Subsystem (IAPS) thruster, were raised from the baseline values of thrust, T = 5 mN, and specific impulse, I sub sp = 2,900s, to thrust, T = 25 mN and specific impulse, I sub sp = 4,300 s. Performance characteristics including estmates of the erosion rates of various component surfaces are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-167887 , NAS 1.26:167887
    Format: application/pdf
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  • 98
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    An application of model testing for the study of rocket exhaust cloud properties (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The application of the 6.4-percent Shuttle Model Test Facility to the study of the Shuttle exhaust cloud properties is discussed with emphasis on the properties related to the production of the deposition (submillimeter drops composed of an acidic liquid and alumina solids) which occurs with each launch. An analysis of test data suggests that the major fraction of the liquid in the deposition is produced directly through the interaction between the exhaust and the deluge water spray and then modified by rapid scavenging of wet acidic aluminum oxide particles. Based on this conclusion, the possibility arises that the acid in the deposition can be neutralized by addition of a base to the deluge water. Current work with the 6.4-percent model is directed toward verification of this hypothesis.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Conference on Aerospace and Aeronautical Meteorology; Jun 06, 1983 - Jun 09, 1983; Omaha, NE
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  • 99
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    Study for analysis of benefit versus cost of low thrust propulsion system (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The benefits and costs associated with placing large space systems (LSS) in operational orbits were investigated, and a flexible computer model for analyzing these benefits and costs was developed. A mission model for LSS was identified that included both NASA/Commercial and DOD missions. This model included a total of 68 STS launches for the NASA/Commercial missions and 202 launches for the DOD missions. The mission catalog was of sufficient depth to define the structure type, mass and acceleration limits of each LSS. Conceptual primary propulsion stages (PPS) designs for orbital transfer were developed for three low thrust LO2/LH2 engines baselined for the study. The performance characteristics for each of these PPS was compared to the LSS mission catalog to create a mission capture. The costs involved in placing the LSS in their operational orbits were identified. The two primary costs were that of the PPS and of the STS launch. The cost of the LSS was not included as it is not a function of the PPS performance. The basic relationships and algorithms that could be used to describe the costs were established. The benefit criteria for the mission model were also defined. These included mission capture, reliability, technical risk, development time, and growth potential. Rating guidelines were established for each parameter. For flexibility, each parameter is assigned a weighting factor.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168011 , NAS 1.26:168011 , MCR-82-521
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    Advanced ion thruster and electrochemical launcher research (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The theoretical model of orificed hollow cathode operation predicted experimentally observed cathode performance with reasonable accuracy. The deflection and divergence characteristics of ion beamlets emanating from a two grid optics system as a function of the relative offset of screen and accel grids hole axes were described. Ion currents associated with discharge chamber operation were controlled to improve ion thruster performance markedly. Limitations imposed by basic physical laws on reductions in screen grid hole size and grid spacing for ion optics systems were described. The influence of stray magnetic fields in the vicinity of a neutralizer on the performance of that neutralizer was demonstrated. The ion current density extracted from a thruster was enhanced by injecting electrons into the region between its ion accelerating grids. Theoretical analysis of the electrothermal ramjet concept of launching space bound payloads at high acceleration levels is described. The operation of this system is broken down into two phases. In the light gas gun phase the payload is accelerated to the velocity at which the ramjet phase can commence. Preliminary models of operation are examined and shown to yield overall energy efficiences for a typical Earth escape launch of 60 to 70%. When shock losses are incorporated these efficiencies are still observed to remain at the relatively high values of 40 to 50%.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168083 , NAS 1.26:168083
    Format: application/pdf
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