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  • Other Sources  (816)
  • SPACECRAFT PROPULSION AND POWER  (816)
  • 1980-1984  (816)
  • 1950-1954
  • 101
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    The Boeing Flywheel Study (1983)
    In:  CASI
    Details
    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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  • 102
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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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  • 103
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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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  • 104
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    Space Station Energy Sizing (1983)
    In:  CASI
    Details
    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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  • 105
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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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  • 106
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    Advanced propulsion for future planetary spacecraft (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: (Previously cited in issue 19, p. 3284, Accession no. A81-40931)
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 107
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    Liquid and solid propulsion system safety design criteria for space transportation system payloads (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Design safety criteria for Space Transportation System propulsion system payloads are discussed. Terms such as inhibit, monitoring, safing, safe distance, safe and arm device, and flow control device are defined and their use in design of safety requirements described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Washington The 1980 JANNAF Propulsion Systems Hazards Subcomm. Meeting, Vol. 1; p 37-41
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  • 108
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    Safety of liquid propulsion systems for STS payloads (1980)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: STS payload safety requirements for Earth-storable liquid propulsion systems are reviewed with respect to applicable safety documents. The effect of normal flight and emergency landing/abort launch profiles on propulsion system design is delineated. Spacecraft studied include Earth satellites, interplanetary spacecraft, and orbit transfer vehicles. Safety considerations for monopropellant (hydrazine), bipropellant (nitrogen tetroxide/monomethyl hydrazine), and ion (mercury) propulsion systems are described. Safety requirements for specific components of propulsion systems are reported. Analysis techniques for STS payload fracture control requirements for pressure vessels and critical support structure are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA, Washington The 1980 JANNAF Propulsion Systems Hazards Subcomm. Meeting, Vol. 1; p 21-35
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  • 109
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    Ion thruster plume effects on spacecraft surfaces (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A charge-exchange plasma, generated by an ion thruster, is capable of flowing upstream from the ion thruster and therefore represents a source of contamination to a spacecraft. An analytical model of the charge-exchange plasma density around a spacecraft was used to estimate the contamination which various spacecraft materials may be exposed to. Measurements of plasma density around an ion thruster were compared to this model. Results of experimental studied regarding the effects on various spacecraft materials' properties due to exposure to expected mercury contamination levels are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 231-241
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  • 110
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    Ion plume/S-band carrier interaction study (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A study was performed to determine the effects of a mercury ion thruster plume on an S-band telecommunication carrier. Experiments were carried out on a 30 cm thruster in a JPL test chamber. Results from simple analytical models were compared with the above measurements and major discrepancies were discovered. Modifications to the electron density model provided a qualitative explanation, but further work is necessary for a quantitative answer. The results indicate the effects of the plume, on S and X Band telecommunications will be minor, with the possible exception of critical angle blockage.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 191-215
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  • 111
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    Electromagnetic interference assessment of an ion drive electric propulsion system (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: An electric propulsion thrust system has the capability of providing a high specific impulse for long duration scientific missions in space. The EMI from the elements of an ion engine was characterized. The compatibility of ion drive electric propulsion systems with typical interplanetary spacecraft engineering was predicted.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 185-190
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  • 112
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    Radiated and conducted EMI from a 30-cm ion thruster (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: In order to properly assess the interaction of a spacecraft with the EMI environment produced by an ion thruster, the EMI environment was characterized. Therefore, radiated and conducted emissions were measured from a 30-cm mercury ion thruster. The ion thruster beam current varied from zero to 2.0 amperes and the emissions were measured from 5 KHz to 200 MHz. Several different types of antennas were used to obtain the measurements. The various measurements that were made included: magnetic field due to neutralizer/beam current loop; radiated electric fields of thruster and plume; and conducted emissions on arc discharge, neutralizer keeper and magnetic baffle lines.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 167-183
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  • 113
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    Facility produced charge-exchange ions (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: These facility produced ions are created by charge-exchange collisions between neutral atoms and energetic thruster beam ions. The result of the electron transfer is an energetic neutral atom and an ion of only thermal energy. There are true charge-exchange ions produced by collisions with neutrals escaping from the ion thruster and being charge-exchange ionized before the neutral intercepts the tank wall. The facility produced charge-exchange ions will not exist in space and therefore, represent a source of error where measurements involving ion thruster plasmas and their density are involved. The quantity of facility produced ions in a test chamber with a 30 cm mercury ion thruster was determined.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 147-166
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  • 114
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    Propagation of charge-exchange plasma produced by an ion thruster (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Under the proper conditions there is an end-effect of a long, cylindrical Langmuir probe which allows a significant increase in collected ion current when the probe is aligned with a flowing plasma. This effect was used to determine the charge-exchange plasma flow direction at various locations relative to the ion thruster. The ion current collected by the probe as a function of its angle with respect to the plasma flow allows determination of the plasma density and plasma flow velocity at the probe's location upstream of the ion thruster optics. The density values obtained from the ion current agreed to within a factor of two of density values obtained by typical voltage-current Langmuir probe characteristics.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 67-72
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  • 115
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    Solar array/spacecraft biasing (1981)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Biasing techniques and their application to the control of spacecraft potential is discussed. Normally when a spacecraft is operated with ion thrusters, the spacecraft will be 10-20 volts negative of the surrounding plasma. This will affect scientific measurements and will allow ions from the charge-exchange plasma to bombard the spacecraft surfaces with a few tens of volts of energy. This condition may not be tolerable. A proper bias system is described that can bring the spacecraft to or near the potential of the surrounding plasma.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Exptl. and Anal. Evaluation of Ion Thruster(Spacecraft Interactions; p 11-28
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  • 116
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    Hydrochloric acid aerosol and gaseous hydrogen chloride partitioning in a cloud contaminated by solid rocket exhaust (1980)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: Partitioning of hydrogen chloride between hydrochloric acid aerosol and gaseous HCl in the lower atmosphere was experimentally investigated in a solid rocket exhaust cloud diluted with humid ambient air. Airborne measurements were obtained of gaseous HCl, total HCl, relative humidity and temperature to evaluate the conditions under which aerosol formation occurs in the troposphere in the presence of hygroscopic HCl vapor. Equilibrium predictions of HCl aerosol formation accurately predict the measured HCl partitioning over a range of total HCl concentrations from 0.6 to 16 ppm.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Atmospheric Environment; 14; 5, 19; 1980
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  • 117
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    Active large structures (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Some performance requirements and development needs for the design of large space structures are described. Areas of study include: (1) dynamic response of large space structures; (2) structural control and systems integration; (3) attitude control; and (4) large optics and flexibility. Reference is made to a large space telescope.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 221-237
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  • 118
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    Some interdisciplinary trade-offs in the design of large space structures (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The constraints placed on the design of large space structures by acceleration, attitude control, and stationkeeping forces are discussed. Stiffness requirements for the structures are derived. The use of active versus passive accuracy control methods is also addressed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 213-219
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  • 119
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    System Requirements and Operations Panel Workshop summary (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The low Earth orbit (LEO) versus the geosynchronous Earth orbit (GEO) deployment systems were discussed. The following items are emphasized: (1) large area systems, such as deployment, altitude, orbit transfer, and on orbit operation; (2) propulsion oriented issues such as the orbit transfer vehicle and the auxiliary propulsion systems; (3) programmatic issues. The LEO versus GEO deployment is a significant driver on propulsion requirements for an orbit transfer vehicle. It is suggested that early systems will be deployed at LEO. The Shuttle remote manipulator system (RMS) will not be involved in early demonstration activities. It is concluded that an integrated large space system/propulsion approach is essential and that propulsion development requirements need to be established.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 135-171
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  • 120
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    Structures-propulsion interactions and requirements (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The effects of low-thrust primary propulsion system characteristics on the mass, area, and orbit transfer characteristics of large space systems (LSS) were determined. Three general structural classes of LSS were considered, each with a broad range of diameters and nonstructural surface densities. While transferring the deployed structure from LEO and to GEO, an acceleration range of 0.02 to 0.1 g's was found to maximize deliverable payload based on structural mass impact. After propulsion system parametric analyses considering four propellant combinations produced values for available payload mass, length and volume, a thrust level range which maximizes deliverable LSS diameter was determined corresponding to a structure and propulsion vehicle. The engine start and/or shutdown thrust transients on the last orbit transfer (apogee) burn can impose transient loads which would be greater than the steady-state loads at the burnout acceleration. The effect of the engine thrust transients on the LSS was determined from the dynamic models upon which various engine ramps were imposed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 81-86
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  • 121
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    Cryogenic orbit transfer vehicle (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Studies determined that shuttle optimized design, allowing the large space system and transfer vehicle in one shuttle flight, greatly reduces transportation costs and minimizes orbital operations. Careful attention to design resulted in efficient payload packaging. A minimum volume, high energy (liquid oxygen and liquid hydrogen) transfer vehicle is described that allows maximum volume for the payload in the orbiter cargo bay.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 43-51
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  • 122
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    Power Systems integration (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Power systems integration in large flexible space structures is discussed with emphasis upon body control. A solar array is discussed as a typical example of spacecraft configuration problems. Information on how electric batteries dominate life-cycle costs is presented in chart form. Information is given on liquid metal droplet generators and collectors, hot spot analysis, power dissipation in solar arrays, solar array protection optimization, and electromagnetic compatibility for a power system platform.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 239-255
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  • 123
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    The 100-meter radiometer spacecraft study (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A rigid body analysis of a baseline Large Space System (LSS) which is to function as a radiometer is presented. The LSS is placed in circular orbit about the Earth at an altitude of 650 km, subjected to environmental and vehicle interaction forces and torques, without an active control system of any type on board. The environment forces and torques are gravity gradient, solar radiation, and aerodynamic. Normal operation is in nadir pointing along the Z-local vertical axis. Orbital velocity is assigned to the x-axis of the spacecraft. The analysis is then used to demonstrate the ability or lack of the gravity gradient torques to stabilize the LSS over one complete orbit.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 173-197
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  • 124
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    System requirements (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Requirements of future space systems, including large space systems, that operate beyond the space shuttle are discussed. Typical functions required of propulsion systems in this operational regime include payload placement, retrieval, observation, servicing, space debris control and support to large space systems. These functional requirements are discussed in conjunction with two classes of propulsion systems: (1) primary or orbit transfer vehicle (OTV) and (2) secondary or systems that generally operate within or relatively near an operational base orbit. Three propulsion system types are described in relation to these requirements: cryogenic OTV, teleoperator maneuvering system and a solar electric OTV.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space System(Propulsion Interactions; p 101-121
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  • 125
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    Structures: Propulsion interactions and requirements (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The dynamics of the interaction of space structures and their propellant systems are outlined. Optimization for a platform type of space structure is discussed. Static and transient loads, propellant accelerations, tolerances, attitude control, and distributed thrust are considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 71-79
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  • 126
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    Electric propulsion: Synergy of orbit transfer and maintenance (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Electric propulsion systems for transferring large payload masses to geosynchronous Earth orbits and providing accurate on-orbit stationkeeping are evaluated. Orbit boosting, inclination change, attitude control, stationkeeping, relocation, disposal, and power sharing on orbits using electric propulsion are compared with the use of chemical propulsion.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 61-69
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  • 127
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    Missions panel workshop summary (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A workshop panel defined missions that would require the potential use of very large, advanced space systems, and ranked them on the basis of need from both a civilian and military perspective. The panel also pointed out those that would need advanced propulsion technology. Surveillance, communications, and defense were given the highest priority, followed by command and control, orbital support, terrestrial support, and space science.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 39-42
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  • 128
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    Potential large space systems mission opportunities for the post 1990's (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Potential mission opportunities outlined and illustrated are missile defense; space defense; command, control, and communications; defense suppression; force support; space transportation; and orbital support.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 19-24
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  • 129
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    NASA space system technology model future mission system needs (1982)
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    Publication Date: 2011-08-18
    Description: The overall technology model is outlined and the objectives and descriptions of the primary and secondary propulsion drives presented. The primary propulsion driver missions are the geostationary platform; the coherent optical system of modular imaging collectors (COSMIC); the 100 meter thinned aperature telescope; and the orbiting deep space relay station (ODSRS). The secondary propulsion driver missions are space platform alpha, the space station, and the automated planetary station.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Propulsion Interactions; p 7-18
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  • 130
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    Free radical propulsion concept (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: (Previously cited in issue 14, p. 2320, Accession no. A81-32905)
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 131
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    Space station power system (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: It is pointed out that space station planning at NASA began when NASA was created in 1958. However, the initiation of the program for a lunar landing delayed the implementation of plans for a space station. The utility of a space station was finally demonstrated with Skylab, which was launched in 1972. In May 1982, the Space Station Task Force was established to provide focus and direction for space station planning activities. The present paper provides a description of the planning activities, giving particular attention to the power system. The initial space station will be required to supply 75 kW of continuous electrical power, 60 kW for the customer and 15 kW for space station needs. Possible alternative energy sources for the space station include solar planar or concentrator arrays of either silicon or gallium arsenide.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Transactions on Aerospace and Electronic Systems (ISSN 0018-9251); AES-20; 666-671
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  • 132
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    High-temperature gaseous oxygen/hydrogen thrusters for space station (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Efforts to determine the critical technologies necessary for the development of a high-temperature GO2/GH2 thruster are reviewed, for space station applications. Two types of thrust chambers are evaluated: one operable at high temperature and the other incorporating regenerative cooling. The high temperature chamber made of rhenium requires minimum cooling of the chamber wall, however, an oxidation barrier should be incorporated to prevent the rhenium thruster from readily oxidizing. The use of rhenium brought about a lower cost, lower weight, and simplicity of fabrication. The igniter-injector, the chamber, the test facility, and the test program are discussed. It is found that an obtained flow split of 58/42 increased the thruster performance from 3893 N-s/Kg to 4030 N-s/Kg for the same chamber pressure and overall mixture ratio. An increase in performance is also observed when the core mixture ratio is lowered. The thruster was tested for 1.9 hrs with no well degradation.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 133
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    Space Shuttle Orbiter improved auxiliary power unit (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The Space Shuttle Orbiter Auxiliary Power Unit subsystem has operated successfully on three vehicles by meeting mission requirements and has proven the design for space operation. The current Auxiliary Power Unit (APU) operational life is limited to 12 missions and the APU turnaround between flights is longer than originally anticipated. The Improved APU objective is to increase life to 50 missions, reduce the three - APU subsystem vehicle weight by 140 lbs., and reduce turnaround time. The design changes incorporated into the Improved APU and the associated development testing are described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: APL The 1984 JANNAF Propulsion Meeting, Vol. 2; p 315-326
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  • 134
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    Measurements of cloud nuclei in the effluents from launches of liquid- and solid-fueled rockets (1982)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Airborne measurements of two types of cloud nuclei, cloud condensation nuclei (CCN) and ice nuclei (IN), were conducted in the stabilized ground clouds which resulted from the launches of a liquid-fueled ATLAS/Centaur rocket and a solid-fueled TITAN III rocket. Results show that the concentrations of CCN in both types of clouds were greater than ambient values for the 2 hours duration of the measurements. The initial production of CCN active at 0.5% supersaturation in the ATLAS and TITAN clouds was found to be equivalent to a 20 and 700 sec emission, respectively, by the city of Denver, Colorado. After the initial production, the clouds continued to generate CCN at a rate of about 1/cu cm sec. However, concentrations of IN in the ATLAS cloud were greater than ambient values for only a short period after launch, and it appears that the nuclei resulted from entrained launch pad and ground debris. The concentrations of IN in the TITAN cloud were found to be at or below ambient levels until about 2 hours after launch when they increased substantially above ambient values.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Applied Meteorology; 21; Sept
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  • 135
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    NASA's laser-propulsion project (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Design concepts, study results, and research directions toward development of CW laser heating of remotely flying spacecraft fuels to provide high impulse thrust are presented. The incident laser radiation would be absorbed by hydrogen through a medium of a laser-supported plasma. The laser energy could be furnished from an orbiting solar-powered laser platform and used to drive the engines of an orbital transfer vehicle (OTV) at costs less than with a chemical propulsion system. The OTV propulsion chamber would be reduced in size comparable to the volume addition of the incident laser energy absorber. The temperatures in the hydrogen-fueled system could reach 5000-15,000 K, and studies have been done to examine the feasibility of ion-electron recombination. Kinetic performance, temperature field, and power necessary to sustain a laser thrust augmented system modeling results are discussed, along with near-term 30 kW CO2 laser system tests.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Astronautics and Aeronautics; 20; Sept
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  • 136
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    Propulsion and fluid management - Station keeping will eat energy on a new scale (1983)
    In:  Other Sources
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    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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  • 137
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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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  • 138
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    Improved ion containment using a ring-cusp ion thruster (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 21; 488-495
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  • 139
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    Integration becomes the name of the OTV game (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Since 1981, NASA has been supporting an Orbit Transfer Vehicle (OTV) propulsion technology development program which encompasses the efforts of three major engine manufacturers. A thrust variability ratio of 30:1 has been stipulated for the baseline 520 lbf-sec/lbm engines, in order to yield the versatility needed for low acceleration missions, orbit-transfer missions, and aeromaneuvering tasks. These goals may not be reachable either individually or collectively; the program supports generic technology benefitting all three engine concepts, as well as concept-specific technology. Engine/vehicle integration will determine the final configuration. The three engines under study differ as to turbomachinery types and operating speeds.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Aerospace America (ISSN 0740-722X); 22; 70-73
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  • 140
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    Technology status report on hydrocarbon-fueled engines for space transportation systems (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Liquid oxygen/hydrocarbon (LOX/HC) fueled engines are being considered for use in future high-pressure engines for launch vehicles and as possible replacements for the orbital maneuvering system and reaction control system engines on the Space Shuttle. High performance, reusability, and low life cycle cost are required for these applications. A technology base for these engines is now being established. This paper provides a review of recent results from LOX/HC technology contracts for the National Aeronautics and Space Administration.
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  • 141
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    A technology data base for the design of 500 to 5000-lb thrust class liquid rocket engines utilizing hydrogen and oxygen as propellants (1982)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: This paper presents an overview of the results of experimental evaluations of candidate designs for igniters, injectors, and propellant-cooled thrust chambers applicable to restartable high-performance, high-reliability upper-stage engines and to pulsing-type reaction control engines (RCE). Injection element types best suited for liquid, gas, and liquid/gas phase propellant supply are identified. The resulting interactions between element type, combustion efficiency, and chamber wall heating are compared. The distinction between thrust chamber design requirements for upper stage vs RCE applications as measured by cycle life requirements is translated into design configurations consisting of all-film-cooled, all-regeneratively-cooled, and composites of the two cooling approaches. The validity of the design approaches is confirmed by data from engine durability testing involving over 90,000 starts and 9,000 thermal cycles on RCE-type designs and multiple long-duration burns (up to 2,000 sec) on regeneratively cooled upper-stage designs.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 142
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    Hydrogen chloride and aerosol ground cloud characteristics resulting from Space Shuttle launches (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: Airborne measurements of gaseous HCl, gaseous and aerosol HCl, particulates, relative humidity and temperature were obtained in ground clouds produced during three Space Shuttle launches. Partitioning of HCl between HCl aerosol and gaseous HCl was investigated as the solid rocket exhaust cloud diluted with ambient air to evaluate the conditions under which aerosol formation occurs in the troposphere in the presence of hygroscopic HCl vapor. Equilibrium predictions for aqueous HCl aerosol formation generally agree with the measured HCl partitioning over HCl concentrations from 0.5 to 36 ppm. HCl concentration dispersion within four cloud segments at time t (min) was evaluated using the expression C = C(0) (t to the alpha power) where C(0) varied from 145 to 2250 ppm and alpha varied from -1.14 to -1.73. Aerosol fallout from the exhaust clouds was measured with time by monitoring HCl concentrations and aerosol distributions 100 m below the cloud as it drifted away from the launch site. Significant amounts of HCl were found to be removed by fallout of particles in the 80-220 micron diameter range up to 30 min after launch.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Atmospheric Environment (ISSN 0004-6981); 18; 4, 19
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  • 143
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    Design, development, performance, and reconditioning of Ni-Cd batteries using polyropylene separators (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: A performance assessment is made for the Viking Mars Lander Program's sealed, sterilizable, 8-ampere hour Ni-Cd batteries, which use a nonwoven polypropylene separator material. Attention is given to separator wettability, the optimization of electrolyte quantity, and the reduction of plate carbonate, in view of thermal considerations and other environmental design and test requirements generated by mission characteristics. Life data based on mission experience identify, in addition to performance and degradation behavior, a series of shallow discharge reconditioning cycles and an intensive program of deep discharge reconditioning.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Journal of Power Sources (ISSN 0378-7753); 12; 305-316
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  • 144
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    LeRC rail accelerators - Test designs and diagnostic techniques (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The feasibility of using rail accelerators for various in-space and to-space propulsion applications was investigated. A 1 meter, 24 sq mm bore accelerator was designed with the goal of demonstrating projectile velocities of 15 km/sec using a peak current of 200 kA. A second rail accelerator, 1 meter long with a 156.25 sq mm bore, was designed with clear polycarbonate sidewalls to permit visual observation of the plasma arc. A study of available diagnostic techniques and their application to the rail accelerator is presented. Specific topics of discussion include the use of interferometry and spectroscopy to examine the plasma armature as well as the use of optical sensors to measure rail displacement during acceleration. Standard diagnostics such as current and voltage measurements are also discussed. Previously announced in STAR as N83-35053
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Transactions on Magnetics (ISSN 0018-9464); MAG-20; 324-327
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  • 145
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    Nuclear electric propulsion (NEP) spacecraft configuration study (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The NEP spacecraft design is for the 100 kWe SP-100 nuclear reactor thermoelectric power supply. Thermoelectric conversion, one of several conversion options being considered for the SP-100, is discussed. Whereas many of the earlier NEP spacecraft designs have been based on highly integrated power and thruster subsystems and have resulted in subsystem requirements that depended largely on the design mission, the SP-100 nuclear power system is a general-purpose power supply. The configuration design must be compatible with this power subsystem design philosophy. The study also detects power and propulsion subsystem integration issues and related technology requirements. It is noted that the new NEP spacecraft design satisfies the most important subsystem integration requirements at the expense of some increase in vehicle inert mass relative to that used in previous studies.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 146
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    Deflagration plasma thruster (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: This paper introduces the application of the magnetized plasma deflagration process to space propulsion. The deflagration process has the unique capability of efficiently converting input energy into kinetic energy in the accelerating direction. To illustrate the totally divergent characters of 'snowplow' detonation and deflagration discharges, examples of the differences between deflagration and detonation 'snowplow' discharges are expressed in terms of current densities, temperature, and particle velocities. Magnetic field profiles of the deflagration mode of discharges are measured. Typical attainable plasma characteristics are described in terms of velocity, electron temperature, and density, as well as measurement techniques. Specific impulses measured by piezo-electric probe and pendulum methods are presented. The influence of the transmission line in the discharge circuits on plasma velocity is measured by means of a microwave time-of-flight method. The results for the deflagration thruster are compared with other space thrusters. Further research areas are identified.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 147
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    Equivalent electron fluence for space qualification of shallow junction heteroface GaAs solar cells (1984)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: It is desirable to perform qualification tests prior to deployment of solar cells in space power applications. Such test procedures are complicated by the complex mixture of differing radiation components in space which are difficult to simulate in ground test facilities. Although it has been shown that an equivalent electron fluence ratio cannot be uniquely defined for monoenergetic proton exposure of GaAs shallow junction cells, an equivalent electron fluence test can be defined for common spectral components of protons found in space. Equivalent electron fluence levels for the geosynchronous environment are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: IEEE Transactions on Electron Devices (ISSN 0018-9383); ED-31; 622-625
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  • 148
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    Thrust for interorbital propulsion - A question of lifetime (1984)
    In:  Other Sources
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    Publication Date: 2011-08-18
    Description: The most promising operational window for the use of magnetoplasmadynamic (MPD) thrusters is identified to be at megawatt power levels for orbital maneuvering. For such applications, the operation of a steady-state MPD thruster system imposes stringent requirements on the lifetime of thruster surfaces which will erode due to interactions with the plasma working fluid. Basic erosion mechanisms are presented and the problems associated with measuring the erosion rates are discussed. An experimental approach that would allow the development of a phenomenological model for erosion is proposed.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 149
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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.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 150
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    Propulsion options for orbit-on-demand vehicles (1984)
    In:  Other Sources
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    Publication Date: 2018-12-01
    Description: Vehicles which can achieve orbit within minutes of a command decision may be needed in the future for a variety of missions. Such orbit-on-demand vehicles may have propulsion requirements that are somewhat different from vehicles designed for routine transportation, but the propulsion evaluation studies of the past need to be considered as a starting point for orbit-on-demand vehicle studies. This paper surveys airbreathing propulsion studies including composite, airturbo-rocket, and scramjet systems and rocket propulsion studies including composite, airturborocket, and scramjet and rocket propulsion studies including dual-fuel and pure hydrocarbon systems. One indication from the results is that a horizontal takeoff airbreathing system with supersonic staging will have a higher development cost than rocket systems primarily because of the cost of the airbreathing engine development. Another indication is that pure hydrocarbon rocket propulsion for a vertical takeoff system may be feasible. Eliminating the requirement for hydrogen fuel may be worthwhile for orbit-on-demand vehicles.
    Keywords: SPACECRAFT PROPULSION AND POWER
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  • 151
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    Performance of a flight qualified, thermoelectrically temperature controlled QCM sensor with power supply, thermal controller and signal processor (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A thermoelectrically temperature controlled quartz crystal microbalance (QCM) system was developed for the measurement of ion thrustor generated mercury contamination on spacecraft. Meaningful flux rate measurements dictated an accurately held sensing crystal temperature despite spacecraft surface temperature variations from -35 C to +60 C over the flight temperature range. An electronic control unit was developed with magentic amplifier transformer secondary power supply, thermal control electronics, crystal temperature analog conditioning and a multiplexed 16 bit frequency encoder.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center The 11th Space Simulation Conf.; p 257-268
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  • 152
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    Photovoltaic technology development for synchronous orbit (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Accomplishments and expected benefits are summarized for the following efforts: (1) achieving silicon solar cell efficiency of 18% at 200 micron m to 250 micron m thickness; (2) reducing silicon cell radiation damage in geosynchronous orbit after 10 years to less than 15%; (3) demonstrating coplanar back contact 50 micron m thick silicon solar cells with efficiency of 14%; (4) demonstrating the feasibility of a radiation tolerant GaAs concentrator cell; (5) achieving 30% efficient photo conversion in the laboratory; (6) defining candidate concepts for 50% efficient electromagnetic conversion; and (7) demonstrating the technology for protecting arrays capable of 300W/kg after 10 years in geosynchronous orbit.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Synchronous Energy Technol.; p 45-56
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  • 153
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    Synchronous energy technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The power program in NASA and DOD are discussed with emphasis on the technology for future large space power systems. The structure of the synchronous energy technology program is described and the technologies required for future geosynchronous power stations are defined. The output of the program is to be a series of design data documents to provide design information and to transfer the technology to the involved community.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Synchronous Energy Technol.; p 1-7
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  • 154
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    Advanced concepts (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The relative strengths of those interactions which enable propulsive forces are listed as well as the specific impulse of various propellants. Graphics show the linear synchronous motor of the mass driver, the principle of the direct current electromagnetic launcher, and the characteristics of the rail gun.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 337-342
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  • 155
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    Electric propulsion for SPS (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design and characteristics of the solar power satellite electric propulsion system are described. Both the payload powered orbital transfer vehicle and the independent powered transfer vehicle configuations are discussed. Mass estimates for the system, the average cost per system unit, and the cost per flight estimates are also given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 229-236
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  • 156
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    Effect of orbital transfer loads on large platforms (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A preliminary automated structural sizing procedure suitable for conceptual design and early tradeoff studies of large truss platforms configured for shuttle transportation to LEO is discussed as well as some orbital transfer design considerations. Platforms that are sized to withstand orbital transfer loads for the LEO to GEO maneuver are compared to platforms sized only for LEO application. It is concluded that for platforms supporting low mass distributed payloads, platform and strut frequency requirements are strong design drivers for LEO applications. The struts are found to be extremely slender, thinswalled, and of small diameter. If full advantage is to be taken of these minimum mass designs, a manufacturing capability must be developed for long straight struts. For platforms that are to be transferred from LEO to GEO in a deployed state, the orbital transfer loads become design drivers. However, even for an initial thrust-to-weight ratio equal to 0.1, a platform on the order of 100 m diameter appears packageable with its OTV in one shuttle flight, and larger platforms appear possible at lower thrust-to-weight ratios.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 143-155
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  • 157
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    Status of nickel-hydrogen cell technology (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Nickel hydrogen cell technology has been developed which solves the problems of thermal management, oxygen management, electrolyte management, and electrical and mechanical design peculiar to this new type of battery. This technology was weight optimized for low orbit operation using computer modeling programs but is near optimum for other orbits. Cells ranging in capacity up to about 70 ampere-hours can be made from components of a single standard size and are available from two manufacturers. The knowledge gained is now being applied to the development of two extensions to the basic design: a second set of larger standard components that will cover the capacity range up to 150 ampere-hours; and the development of multicell common pressure vessel modules to reduce volume, cost and weight. A manufacturing technology program is planned to optimize the producibility of the cell design and reduce cost. The most important areas for further improvement are life and reliability which are governed by electrode and separator technology.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 97-105
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  • 158
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    Influence of interorbit acceleration on the design of large space antennas (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The characteristics of the acceleration-induced loading in structures consisting of triangular lattices are investigated and some initial quantitative results on the effect on the design mass and stowage volume are presented. The approach used defines the structural design that would be used if no interorbit acceleration were required and then determines what strengthening would be required to accommodate the loads due to acceleration. The basic zero acceleration design can be based on the stringent accuracy requirements placed on the antennas.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 157-178
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  • 159
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    Large space systems technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Technical challenges of shuttle-era large space systems include the development of space-configured spacecraft concepts, compatibility with the space transportation system, and cost effectiveness. The objectives and organization of NASA's large space structures program are outlined and program elements are discussed. The technology for the offset wrap-rip and the maypole (hoop/column) antenna concepts are discussed as well as analysis techniques for predicting the electromagnetic performance of a broad class of large reflectors. Deployable systems, assembly methods, and modular control systems for space platforms are described. Assembly equipment and devices, surface sensors and shape control, control and stabilization, and integrated analysis and design are also considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 9-22
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  • 160
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    IUS solid rocket motor contamination prediction methods (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A series of computer codes were developed to predict solid rocket motor produced contamination to spacecraft sensitive surfaces. Subscale and flight test data have confirmed some of the analytical results. Application of the analysis tools to a typical spacecraft has provided early identification of potential spacecraft contamination problems and provided insight into their solution; e.g., flight plan modifications, plume or outgassing shields and/or contamination covers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Johnson Space Center The 11th Space simulation Conf.; p 243-256
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  • 161
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    Electrochemical Orbital Energy Storage (ECOES) technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The versatility and flexibility of a regenerative fuel cell power and energy storage system is considered. The principal elements of a Regenerative Fuel Cell System combine the fuel cell and electrolysis cell with a photovoltaic solar cell array, along with fluid storage and transfer equipment. The power output of the array (for LEO) must be roughly triple the load requirements of the vehicle since the electrolyzers must receive about double the fuel cell output power in order to regenerate the reactants (2/3 of the array power) while 1/3 of the array power supplies the vehicle base load. The working fluids are essentially recycled indefinitely. Any resupply requirements necessitated by leakage or inefficient reclamation is water - an ideal material to handle and transport. Any variation in energy storage capacity impacts only the fluid storage portion, and the system is insensitive to use of reserve reactant capacity.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 81-95
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  • 162
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    Air Force space power technology program (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The military spacecraft power subsystem design requirements, developments goals, and planned technology efforts are summarized. The mission drivers of performance (weight and volume), hardening (survivability), autonomy, reliability, and miniaturization influence space mission effectiveness are outlined. The anticipated performance versus power level trends for reactor static conversion systems are illustrated. A conceptual design for a space based radar system is also given.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 15-28
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  • 163
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    Low-thrust chemical propulsion (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Results from investigations leading to the definition of low thrust chemical engine concepts are described. From the thrust chamber cooling analyses, regenerative/radiation-cooled LO2/H2 thrust chambers offered the largest thrust and chamber pressure operational envelope primarily due to the superior cooling capability of hydrogen and its low critical pressure. Regenerative/radiation-cooled LO2/CH4 offered the next largest operational envelope. The maximum chamber pressure for film/radiation-cooling was significantly lower than for regenerative/radiation-cooling. As in regeneration-cooling, LO2/H2 thrust chambers achieved the highest maximum chamber pressure, LO2/CH4 film/radiation-cooling was found not feasible and LO2/RP-1 film/radiation-cooling was extremely limited. In the engine cycle/configuration evaluation, the engine cycle matrix was defined through the incorporation of the heat transfer results. Engine cycle limits were established with the fuel-cell power cycle achieving the highest chamber pressure; however, the fuel cell system weights were excessive. The staged combustion cycle achieved the next highest chamber pressure but the preburner operational feasibility was in question.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 263-286
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    Low-thrust vehicle concept studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Part of NASA's orbit transfer vehicle propulsion program is devoted to the development of analytical tools to define propulsion system performance, weight, size, and other parameters, and to develop packing concepts for LSS mission propulsion and payload systems. Packing studies discussed relate to shuttle cargo bay constraints; low thrust engine profile and performance; large space frame concept and weight; low thrust vehicles stowed in shuttle, LSS payload capability, and weight distribution. Further study is needed to determine interactions among propulsion system, payload structures, and shuttle. Low thrust-to-weight ratios are desirable to maximize payload weights and deployed areas.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 97-106
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  • 165
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    Power management (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The multihundred kW power system management and a distribution program aims to develop critical components, circuits, and subsystems required to manage the generation, storage, and distribution of energy in large, orbital space systems. To accomplish this objective, a reference system including subsystems for the generation and storage of energy and management of electrical and thermal energy was designed and is being used to assess at the system level the impact of changing various subsystem parameters. A power management subsystem will then be designed. The subsystem is autonomous and based on ground utility systems concepts to the maximum extent possible. An agency power system breadboard is under development for characterizing and verifying the various component and subsystem technology developments.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 107-114
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  • 166
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    Large solar arrays (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A spectrophotovoltaic converter, a thermophotovoltaic converter, a cassegrainian concentrator, a large silicon cell blanket, and a high flux approach are among the concepts being investigated as part of the multihundred kW solar array program for reducing the cost of photovoltaic energy in space. These concepts involve a range of technology risks, the highest risk being represented by the thermophotovoltaics and spectrophotovoltaics approaches which involve manipulation to of the incoming spectrum to enhance system efficiency. The planar array (solar blanket) has no technology risk and a moderate payback. The primary characteristics, components, and technology concerns of each of these concepts are summarized. An orbital power platform mission in the late 1980's is being used to allow a coherent technology advancement program in order to achieve a ten year life with maintenance at a capital recurring cost of $30/watt based on 1978 dollars.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Space Flight Center Synchronous Energy Technol.; p 57-68
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  • 167
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    Electric propulsion and power (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The development of electric propulsion systems is discussed and the benefits of these systems to various space mission requirements are outlined. The characteristics and development status of 8 and 30 cm mercury ion thrusters and solar electric propulsion systems are reported. In addition the advantages of an inert gas thruster for Earth orbital missions are examined and include its capability for operation at higher values of specific impulse, the ease at which it can be integrated with space systems, and it's low pollution potential.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 219-228
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  • 168
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    Chemical propulsion technology (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An overview of NASA's low thrust liquid chemical propulsion program is presented with particular emphasis on thrust system technology in the ten to one thousand pound thrust range. Key technology issues include high performance of cooled low thrust engines; small cryogenic pumps; multiple starts-shutdowns (10) with slow ramps (approximately 10 seconds); thrust variation - 4/1 in flight and 20/1 between flights; long life (100 hours); improved system weight and size; and propellant selection.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 31-36
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  • 169
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    Orbital transfer vehicle engine integration study (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: NASA-LeRC is sponsoring industry studies to establish the technology base for an advanced engine for orbital transfer vehicles for mid-1990s IOC. Engine contractors are being assisted by vehicle contractors to define the requirements, interface conditions, and operational design criteria for new LO2-LH2 propulsion systems applicable to future orbit transfer vehicles and to assess the impacts on space basing, man rating, and low-G transfer missions on propulsion system design requirements. The results of a study is presented. The primary study emphasis was to determine what the OTV engine thrust level should be, how many engines are required on the OTV, and how the OTV engine should be designed. This was accomplished by evaluating planned OTV missions and concepts to determine the requirements for the OTV propulsion system, conducting tradeoffs and comparisons to optimize OTV capability, and evaluating reliability and maintenance to determine the recommended OTV engine design for future development.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-174842 , NAS 1.26:174842 , GDC-SP-84-050
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  • 170
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    Solid-propellant rocket motor internal ballistics performance variation analysis, phase 5 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of research aimed at improving the predictability of internal ballistics performance of solid-propellant rocket motors (SRM's) including thrust imbalance between two SRM's firing in parallel are presented. Static test data from the first six Space Shuttle SRM's is analyzed using a computer program previously developed for this purpose. The program permits intentional minor design biases affecting the imbalance between any two SMR's to be removed. Results for the last four of the six SRM's, with only the propellant bulk temperature as a non-random variable, are generally within limits predicted by theory. Extended studies of internal ballistic performance of single SRM's are presented based on an earlier developed mathematical model which includes an assessment of grain deformation. The erosive burning rate law used in the model is upgraded and made more general. Excellent results are obtained in predictions of the performances of five different SRM's of quite different sizes and configurations. These SRM's all employ PBAN type propellants with ammonium perchlorate oxidizer and 16 to 20% aluminum except one which uses carboxyl terminated butadiene binder. The only non-calculated parameters in the burning rate equations that are changed for the different SRM's are the zero crossflow velocity burning rate coefficients and exponents. The results, in general, confirm the importance of grain deformation. The improved internal ballistic model makes practical development of an effective computer program for application of an optimization technique to SRM design which is also demonstrated. The program uses a pattern search technique to minimize the difference between a desired thrust-time trace and one calculated based on the internal ballistic model.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-177145 , NAS 1.26:177145
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  • 171
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    Dynamic Conversion Working Group Summary (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-13
    Description: The potential of dynamic conversion devices for use in solar and nuclear dynamic space power systems was addressed. Conversion systems considered were based on the use of Brayton, Stirling and Rankine cycles. Both organic and liquid metal Rankine cycles were included. The basic system considerations were: mission requirements, system attributes, system options, technology issues and constraints, and priorities of needed technology development. Mission requirements, where dynamic conversion was considered enabling technology, were identified along with the associated power levels and potential energy sources. When considering the system options special attention was given to recommend operating temperatures and other significant discriminators. A list of prioritized tasks considered important for the successful development of dynamic conversion systems for 1995 and beyond was compiled.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 297-299
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  • 172
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    Advanced and Nontraditional Concepts Working Group Report (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-13
    Description: Advanced and nontraditional concepts relating to future space power requirements were examined with special emphasis on the requirements for the space station. Key findings in the following ares are outlined: dynamic radiation concepts, space nuclear reactors, energy conversion cycles, beam power transmission, electrodynamic tethers and advanced photovoltaics.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 327-335
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  • 173
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    Electrical System Technology Working Group (WG) Report (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-13
    Description: The technology needs for space power systems (military, public, commercial) were assessed for the period 1995 to 2005 in the area of power management and distribution, components, circuits, subsystems, controls and autonomy, modeling and simulation. There was general agreement that the military requirements for pulse power would be the dominant factor in the growth of power systems. However, the growth of conventional power to the 100 to 250kw range would be in the public sector, with low Earth orbit needs being the driver toward large 100kw systems. An overall philosophy for large power system development is also described.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 317-321
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  • 174
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    Electrodynamic Tethers. 1: Power Generator in LEO. 2: Thrust for Propulsion and Power Storage (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-13
    Description: An electrodynamic tether consists of a long insulated wire in space whose orbital motion cuts across lines of magnetic flux to produce an induce voltage that in typical low orbits averages about 200 v/km. Such a system should be capable of generating substantial electrical power, at the expense of IXB drag acting on its orbital energy. If a reverse current is driven against the induced voltage, the system should act as a motor producing IXB thrust. A reference system was designed, capable of generating 20 KW of power into an electrical load located anywhere along the wire at the expense of 2.6N (20,000 J/sec) drag on the wire. In an ideal system, the conversion between mechanical and electrical energy would reach 100% efficiency. In the actual system part of the 20 KW is lost to internal resistance of the wire, plasma and ionosphere, while the drag force is increased by residual air drag. The 20 KW PMG system as designed is estimated to provide 18.7 KW net power to the load at total drag loss of 20.4 KJ/sec, or an overall efficiency of 92%. Similar systems using heavier wire appear capable of producing power levels in excess of 1 Megawatt at voltages of 2-4 KV, with conversion efficiency between mechanical and electrical power better than 95%. The hollow cathode based system should be readily reversible from generator to motor operation by driving a reverse current using onboard power.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 275-284
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  • 175
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    Heat Rejection Working Group Synopsis (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-13
    Description: Heat rejection system requirements of specific mission types (space station, planetary exploration, commercial, very high power, and military missions) are discussed. Heat pipe radiators, weight and volume reduction, stable coatings, and working fluids are addressed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 309-316
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  • 176
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    The Liquid Droplet Radiator - an Ultralightweight Heat Rejection System for Efficient Energy Conversion in Space (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-13
    Description: A heat rejection system for space is described which uses a recirculating free stream of liquid droplets in place of a solid surface to radiate waste heat. By using sufficiently small droplets ( 100 micron diameter) of low vapor pressure liquids the radiating droplet sheet can be made many times lighter than the lightest solid surface radiators (heat pipes). The liquid droplet radiator (LDR) is less vulnerable to damage by micrometeoroids than solid surface radiators, and may be transported into space far more efficiently. Analyses are presented of LDR applications in thermal and photovoltaic energy conversion which indicate that fluid handling components (droplet generator, droplet collector, heat exchanger, and pump) may comprise most of the radiator system mass. Even the unoptimized models employed yield LDR system masses less than heat pipe radiator system masses, and significant improvement is expected using design approaches that incorporate fluid handling components more efficiently. Technical problems (e.g., spacecraft contamination and electrostatic deflection of droplets) unique to this method of heat rejectioon are discussed and solutions are suggested.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 261-274
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    Effects of the Solar and Extraterrestrial Environments on Space Power Systems (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: Environments surrounding the major extraterrestrial bodies in the solar system and their interactions with spacecraft power systems are summarized. The environments associated with neutrals/dust, low energy plasma, and where applicable, magnetospheres are discussed for a wide variety of cases. The impact of these environments on power systems - in particular, radiation effects, spacecraft charging, plasma interactions, surface sputtering/erosion, and induced currents - are presented. As power systems must be designed to survive in these hostile environments, it is important that they be taken into account in planning future power systems.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 225-249
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  • 178
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    Analytical Modeling of Spacecraft Power Systems (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: During the 25 years of space flight with unmanned Earth orbiting satellites, there has been an evolution of power systems in three general areas. The size of power system in terms of power demand at the bus has increased frorm a few watts in the early 1960s to a few hundred watts during the 1970s. Today, the bus power requirements are typically in the .5 to 1 kw range with some mission requirements exceeding the 1 kw size. Power grounding and user isolation are major design considerations when high fidelity power is required by a user.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 219-223
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  • 179
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    Space Power Management and Distribution Status and Trends (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: An overview of space power management and distribution (PMAD) is provided which encompasses historical and current technology trends. The PMAD components discussed include power source control, energy storage control, and load power processing electronic equipment. The status of distribution equipment comprised of rotary joints and power switchgear is evaluated based on power level trends in the public, military, and commercial sectors. Component level technology thrusts, as driven by perceived system level trends, are compared to technology status of piece-parts such as power semiconductors, capacitors, and magnetics to determine critical barriers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 205-218
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  • 180
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    Power for Commercial Space Applications (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: Since the proposed space station is intended to be a permanent installation, used in part by commercial organizations, its design requirements differ fundamentally from those in previous manned spacecraft. In particular, commercialization on a significant scale depends critically on the ability to control capital and operational costs, including the cost of energy, and this demands new approaches to systems such as the power supply for the space station. These considerations suggest guidelines for power plant development. The cost of energy in space, guidelines for power supply development, quality standards, and the role of government are discussed.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 37-44
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  • 181
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    Space Power for Communication Satellites Beyond 1995 (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: The space power trends for communication satellites beginning in the mid-70's are reviewed. Predictions of technology advancements and requirements were compared with actual growth patterns. The conclusions derived suggest that the spacecraft power system technology base and present rate of advancement will not be able to meet the power demands of the early to mid-90's. It is recommended that an emphasis on accelerating the technology development be made to minimize the technology gap.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 31-36
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  • 182
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    Emerging Space Nuclear Power Needs (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-12
    Description: Growing interest in new classes of military and civil space systems which demand substantial increases in power over current satellites is generating a renewed interest in space qualified nuclear power systems. Indeed, one can say that power is a limiting technology to the achievement of many future goals in space. The speed of nuclear power system development is currently limited by the lack of a clear distinct definition of system requirements. Emerging system requirements are discussed for the following fields: robust surveillance systems, survivable communication systems with anti-jam capabilities, electric propulsion systems, and weapons applications.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space power; p 27-30
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  • 183
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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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  • 184
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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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  • 185
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    Advanced Concepts Liquid Droplet Radiator (1984)
    In:  CASI
    Details
    Publication Date: 2014-09-13
    Description: An exploratory point design study was carried out on a shuttle-launchable megawatt nuclear orbit transfer vehicle (OTV) with a 5000 kg payload capacity. The system, which consists of a fixed bed reactor, a Brayton cycle power conversion system, and a liquid droplet radiator (LDR) to reject heat, is deployable from a small package. The methods and technologies of this design are discussed, as well as critical design problems. While this is a preliminary study, it indicates that a space-nuclear reactor, combined with the LDR, make possible a continuous 10 MW(e) power station on orbit with a single shuttle launch.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 251-260
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  • 186
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    Electric propulsion technology (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The advanced electric propulsion program is directed towards lowering the specific impulse and increasing the thrust per unit of ion thruster systems. In addition, electrothermal and electromagnetic propulsion technologies are being developed to attempt to fill the gap between the conventional ion thruster and chemical rocket systems. Most of these new concepts are exagenous and are represented by rail accelerators, ablative Teflon thrusters, MPD arcs, Free Radicals, etc. Endogenous systems such as metallic hydrogen offer great promise and are also being pursued.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 23-30
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  • 187
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    Design and development of the quad redundant servoactuator for the space shuttle solid rocket booster thrust vector control (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The design and theory of operation of the servoactuator used for thrust vector control of the space shuttle solid rocket booster is described accompanied by highlights from the development and qualification test programs. Specific details are presented concerning major anomalies that occurred during the test programs and the corrective courses of action pursued.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center Proc. of the 14th Aerospace Mech. Symp.; p 125-141
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  • 188
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    LSS/propulsion interactions studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Interactions between the LSS and the propulsion system are large, significant, interrelated, and complex. Issues and problems in interfacing include the effects on the structure from static, dynamic, and launch loads, control, thrust distribution, throttling, and the environment. Control interaction, the disposal of debris/obsolete spacecraft, and the constraints of launch to low Earth orbit must also be considered.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Large Space Systems(Low-Thrust Propulsion Technol.; p 37-52
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  • 189
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    Low-thrust vehicles concept studies (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Low thrust chemical (hydrogen-oxygen) propulsion systems configured specifically for low acceleration orbit transfer of large space systems were studied in order to provide the required additional data to better compare new, low thrust chemical propulsion systems with other propulsion approaches such as advanced electric systems. Study results indicate that it is cost-effective and least risk to combine the low thrust OTV and stowed spacecraft in a single 65 K shuttle. Mission analysis indicates that there are 25 such missions, starting in 1987. Multiple shuttles (LSS in one, OTV in another) result in a 20% increase in LSS (SBR) diameter over single shuttle launches. Synthesis and optimization of the LSS characteristics and OTV capability resulted in determination of the optimum thrust-to-weight and thrust level. For the space based radar with radial truss arms (center thrust application), the optimum thrust-to-weight (maximum) is 0.1, giving a thrust of 2000 lb. For the annular truss (edge-on thrust application) the structure is not as sensitive, and thrust of 1000 lb appears optimum. For the geoplatform, optimum T/W is .15 (3000 lb thrust). The effects of LSS structure material, weight distribution, and unit area density were evaluated, as were the OTV engine thrust transient and number of burns.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Large Space Systems(Low-Thrust Propulsion Technol.; p 73-96
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  • 190
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    Results of tests of MTA-2 TPS on the SRB hold-down bolt blast container (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The four solid rocket booster (SRB) hold-down posts are fastened to the mobile launch platform (MLP) with four large nuts. At liftoff the nuts are split with explosive changes to release the SRB/Shuttle. A blast container is placed over the nuts to protect the vehicle from flying debris. The blast container is a reusable part and has to be protected from aerodynamic heating during flight. The thermal protection system (TPS) used to protect these blast containers is cork. Fitting the flat cork sheet to this hemispherical shaped blast container is both time consuming and expensive. Another problem is removing the charred cork and epoxy glue from the blast containers. Replacements of this cork with another TPS material such as MTA-2 was examined. Heating rates along the centerline of the forward facing areas of the blast container were determined. The feasibility of using 1/2 in. MTA-2 on the SRB blast containers for protection from ascent, plume impingement and reentry heating is demonstrated.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170891 , NAS 1.26:170891 , LMSC-HREC-TN-D867571
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  • 191
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    Results of tests on a specimen of the SRB aft skirt heat shield curtain in the MSFC LRLF (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A full scale segment of the actual Solid Rocket Booster aft skirt heat shield curtain was tested in the Large Radiant Lamp Facility (LRLF) at Marshall Space Flight Center. The curtain was mounted in the horizontal position in the same manner as it is to be mounted on the SRB. A shaker rig was designed and used to provide a motion of the curtain, simulating that to be caused in flight by vehicle acoustics. Thermocouples were used to monitor curtain materials temperatures. Both ascent and reentry heat loads were applied to the test specimen. All aspects of the test setup performed as expected, and the test was declared successful.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-170883 , NAS 1.26:170883 , LMSC-HREC-TM-D697896
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  • 192
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    Atomization data requirements for rocket combustor modeling (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The complex computer codes, which model liquid rocket combustors, require information about the distribution and atomization of these liquid reactants. The available information is, in general, of questionable validity and applicability. Authors and users of combustion codes are often unaware of, or underestimate the importance of, these deficiencies in atomization data. These deficiencies and their importance are examined. Results of analyses performed with a state-of-the-art rocket combustion code are presented which demonstrate the important effects of such atomization information as initial droplet sizes and size distribution on vaporization rate and losses. Also, the questionable aspects and inapplicability of the available atomization data are discussed. One important and often neglected or misunderstood aspect of atomization data is the differences between spatial (concentration) and flux (often called temporal) droplet size distributions. These are described, and a computer model constructed to assess the difference between concentration and flux droplet size distributions is described and results presented. Experimental data are also given to demonstrate this difference. Finally, experimental results are presented that demonstrate the very great, and often neglected effect, of the local gas velocity field on atomization.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: APL 21st JANNAF Combust. Meeting, Vol. 1; p 369-377
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  • 193
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    Ring-cusp ion thruster with shell anode (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An improved ion thruster for low specific impulse operation in the 1500 sec to 6000 sec range has a multicusp boundary field provided by high strength magnets on an iron anode shell which lengthens the paths of electrons from a hollow cathode assembly. A downstream anode pole piece in the form of an iron ring supports a ring of magnets to provide a more uniform beam profile. A cylindrical cathode magnet can be moved selectively in an axial direction along a feed tube to produce the desired magnetic field at the cathode tip.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NAS 1.71:LEW-13881-1
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  • 194
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    Analysis of large solid propellant rocket engine exhaust plumes using the direct simulation Monte Carlo method (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new solution procedure has been developed to analyze the flowfield properties in the vicinity of the Inertial Upper Stage/Spacecraft during the 1st stage (SRMI) burn. Continuum methods are used to compute the nozzle flow and the exhaust plume flowfield as far as the boundary where the breakdown of translational equilibrium leaves these methods invalid. The Direct Simulation Monte Carlo (DSMC) method is applied everywhere beyond this breakdown boundary. The flowfield distributions of density, velocity, temperature, relative abundance, surface flux density, and pressure are discussed for each species for 2 sets of boundary conditions: vacuum and freestream. The interaction of the exhaust plume and the freestream with the spacecraft and the 2-stream direct interaction are discussed. The results show that the low density, high velocity, counter flowing free-stream substantially modifies the flowfield properties and the flux density incident on the spacecraft. A freestream bow shock is observed in the data, located forward of the high density region of the exhaust plume into which the freestream gas does not penetrate. The total flux density incident on the spacecraft, integrated over the SRM1 burn interval is estimated to be of the order of 10 to the 22nd per sq m (about 1000 atomic layers).
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-0496
    Format: text
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  • 195
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    Aluminum chloride formation on Space Shuttle aluminum oxide (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Samples of particulates collected from the exhaust of Space Shuttle launches STS-1, -4, -5, -6, and -7 were analyzed. Scanning electron microscopy and X-ray diffractometry of these samples indicated that the particulates were spherical and predominantly composed of aluminum oxide. The water-soluble weight fraction, pH, acid-soluble weight fraction, and insoluble weight fraction were determined for each sample. Water-soluble weight fractions averaged about 7 percent of the total sample weight, were generally very acidic, and contained significantly elevated concentrations of chloride and aluminum (III) ion. The high concentrations of soluble aluminum (III) and chloride ions observed suggested that aluminum chlorides and/or oxychlorides had formed on the surface of the alumina particulates. More than 72 percent by weight of each sample was insoluble in either water or strong mineral acid, and was identified as alpha-Al2O3. The results from these analyses suggest that the surface of Space Shuttle exhaust alumina particulates will be highly acidic and heavily chlorided, and that a substantial amount of the surface chloride may be chemically associated with aluminum (III) ions rather than just physically adsorbed as HCl.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-0469
    Format: text
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  • 196
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    A comparison of the efficiency of numerical methods for integrating chemical kinetic rate equations (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The efficiency of several algorithms used for numerical integration of stiff ordinary differential equations was compared. The methods examined included two general purpose codes EPISODE and LSODE and three codes (CHEMEQ, CREK1D and GCKP84) developed specifically to integrate chemical kinetic rate equations. The codes were applied to two test problems drawn from combustion kinetics. The comparisons show that LSODE is the fastest code available for the integration of combustion kinetic rate equations. It is shown that an iterative solution of the algebraic energy conservation equation to compute the temperature can be more efficient then evaluating the temperature by integrating its time-derivative.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: APL Computational Methods. 1984 JPM Spec. Session; p 69-82
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  • 197
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    The annular flow electrothermal ramjet (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The annular flow, electrothermal, plug ramjet is examined as a possible means of achieving rapid projectile acceleration to velocities for such applications as direct launch of spacebound payloads. The performance of this ramjet operating with hydrogen propellant is examined for cases where this working fluid is treated: (1) as a perfect gas, and (2) as a gas that is allowed to dissociate and ionize and then recombine with finite reaction rates in the nozzle. Performance results for these cases are compared to the performance of a conventional ramjet operating with perfect gas hydrogen propellant. The performance of the conventional ramjet is superior to that of the annular flow, electrothermal ramjet. However, it is argued that the mechanical complexities associated with conventional ramjet operation are difficult to attain, and for this reason the annular flow, electrothermal ramjet is more desirable as a launch system. Models are presented which describe both electrothermal plug ramjet and conventional ramjet operation, and it is shown that for a given flight velocity there is a rate of heat addition per unit propellant mass for which ramjet operation is optimized.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-174704 , NAS 1.26:174704
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  • 198
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    Ion beamlet steering for two-grid electrostatic thrusters (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experimental study of ion beamlet steering in which the direction of beamlets emitted from a two grid aperture system is controlled by relative translation of the grids, is described. The results can be used to design electrostatic accelerating devices for which the direction and focus of emerging beamlets are important. Deflection and divergence angle data are presented for two grid systems as a function of the relative lateral displacement of the holes in these grids. At large displacements, accelerator grid impingements become excessive and this determines the maximum allowable displacement and as a result the useful range of beamlet deflection. Beamlet deflection is shown to vary linearly with grid offset angle over this range. The divergence of the beamlets is found to be unaffected by deflection over the useful range of beamlet deflection. The grids of a typical dished grid ion thruster are examined to determine the effects of thermally induced grid distortion and prescribed offsets of grid hole centerlines on the characteristics of the emerging beamlets. The results are used to determine the region on the grid surface where ion beamlet deflections exceed the useful range. Over this region high accelerator grid impingement currents and rapid grid erosion are predicted.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-174671 , NAS 1.26:174671
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  • 199
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    Preliminary engineering report for design of a subscale ejector/diffuser system for high expansion ratio space engine testing (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design of a subscale jet engine driven ejector/diffuser system is examined. Analytical results and preliminary design drawings and plans are included. Previously developed performance prediction techniques are verified. A safety analysis is performed to determine the mechanism for detonation suppression.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-171137 , NAS 1.26:171137 , LMSC-HREC-TR-D951414
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  • 200
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    NASA Orbit Transfer Rocket Engine Technology Program (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The advanced expander cycle engine with a 15,000 lb thrust level and a 6:1 mixture ratio and optimized performance was used as the baseline for a design study of the hydrogen/oxgyen propulsion system for the orbit transfer vehicle. The critical components of this engine are the thrust chamber, the turbomachinery, the extendible nozzle system, and the engine throttling system. Turbomachinery technology is examined for gears, bearing, seals, and rapid solidification rate turbopump shafts. Continuous throttling concepts are discussed. Components of the OTV engine described include the thrust chamber/nozzle assembly design, nozzles, the hydrogen regenerator, the gaseous oxygen heat exchanger, turbopumps, and the engine control valves.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-168156 , NAS 1.26:168156
    Format: application/pdf
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