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  • Other Sources  (4,196)
  • PROPULSION SYSTEMS  (1,456)
  • COMMUNICATIONS  (1,377)
  • THERMODYNAMICS AND COMBUSTION  (1,363)
  • General Chemistry
  • 1970-1974  (4,196)
Collection
Source
Keywords
Years
Year
  • 1
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    Ablator manufacturing (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Studies are being conducted to determine how manufacturing-induced defects affect the performance of ablative heat shields. If commonly occurring defects do not affect material performance, simpler manufacturing techniques can be used, quality control requirements can be relaxed, repair and rework operations can be held to a minimum, and thus the total manufacturing cost can be reduced.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 475-504
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  • 2
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    Antenna drive system for the Nimbus satellite (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A two-axis drive system is described for pointing a high gain antenna. Motion about each axis is provided by identical drive mechanisms. Only three gear passes are required to obtain the necessary 900:1 gear reduction. The drive system is a primary element of an experiment that will provide a real time data link between Nimbus and ground stations. Data are transmitted from Nimbus to the applications technology satellite, which relays the data to ground stations.
    Keywords: COMMUNICATIONS
    Type: NASA. Ames Res. Center 6th Aerospace Mech. Symp.; p 117-120
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  • 3
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    The Intelsat 4 antenna positioner (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The Intelsat 4 communications satellite has two spot beam antennas which are pointed to selected land masses by gimbaled positioners. The positioners employ drive motors with electromagnetic brakes and jackscrews that are self-caging during the launch. The positioner uses dry lubricants for ball bearings, spur gears, screw and nut, and various journal bearings. A coefficient of friction of approximately 0.05 was demonstrated in vacuum operation. Success of the positioner was demonstrated on the first Intelsat 4 placed in orbit in January 1971. The developmental problems that were encountered and their solutions are discussed.
    Keywords: COMMUNICATIONS
    Type: NASA. Ames Res. Center 6th Aerospace Mech. Symp.; p 109-116
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  • 4
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    Locations of solar radio bursts (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Measurements of the positions of the sources of solar radio bursts at decameter wavelengths, 20- to 60-MHz range, provide information about physical conditions in a region of the corona extending from about one-half to several solar radii from the surface of the sun. Position measurements in the 20- to 60-MHz range were made with the Clark Lake sweep-frequency grating interferometer. Although the resolution of the instrument is sufficient to measure source position accurately, the highly variable effect of refraction in the earth's ionosphere severely limits the observations, distorting position determinations to such an extent as to make much of the position data useless unless ionospheric refraction can be taken into account. A method was developed for the removal of the refractive effect from the data to permit determination of true source position. With this technique it is considered possible to measure spatial extent of radio sources that will provide information about emission processes and physical parameters in the corona.
    Keywords: COMMUNICATIONS
    Type: Significant Accomplishments in Sci., 1970; p 149-153
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  • 5
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    Manufacturing developments in insulation application (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Manufacturing development studies have been conducted to provide information on the fabrication and handling characteristics of a number of candidate multilayer insulation systems. The application of these complex, lightweight insulation systems to large-scale, flight-type cryogenic tankage and other structures has of necessity required the development of new methods, processes, and tooling concepts. Results of some of the studies that have contributed to the advancement of cryogenic technology are presented. The insulation systems that are of primary importance for future application are those using the sliced foam spacers, the net type spacers, the glass fiber paper spacers, and the Superfloc system which consists of tufts of dacron fibers flocked on the surface of the radiation shields.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 73-92
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  • 6
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    Design for advanced insulation systems (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The design of principal multilayer insulation (MLI) systems being investigated by Marshall Space Flight Center and its contractors for application to flight-type cryogenic tankage for long-term storage in space vehicles is described. The MLI systems were designed for application to a 105 in. diameter cryogenic test tank to simulate full-scale design and installation methods representative of flight-type hardware. The MLI systems selected for design represent systems suitable for use on space vehicles such as the modular nuclear vehicles that require application of thicknesses up to 6 in. The MLI systems are lightweight and structurally efficient.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 53-72
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  • 7
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    Multilayer high performance insulation materials (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A number of tests are required to evaluate both multilayer high performance insulation samples and the materials that comprise them. Some of the techniques and tests being employed for these evaluations and some of the results obtained from thermal conductivity tests, outgassing studies, effect of pressure on layer density tests, hypervelocity impact tests, and a multilayer high performance insulation ambient storage program at the Kennedy Space Center are presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. At MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 93-98
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  • 8
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    Reduction of near-in sidelobes using phase reversal aperture rings (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A technique is described for reducing near-in sidelobes in spacecraft antennas by cancellation. This technique takes a small portion of the radiation from the antenna aperture and generates the near-in lobes, which are then fed out of phase relative to the main signal. Results of sample cases indicate that the first three lobes can be nearly eliminated at a 40% reduction in aperture efficiency.
    Keywords: COMMUNICATIONS
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 34-42
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  • 9
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    Fire extinguishment in hypobaric and hyperbaric environments (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Work that has been performed to provide information on the effects of various fire extinguishing agents in special atmospheres is discussed. Data used in the development of both equipment and techniques for manned spacecraft and related equipment are discussed. The equipment includes a hypobaric chamber suitable for low pressure use and a hyperbaric chamber for high pressure operation. The effectiveness of agents in weightless environment is also discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 163-169
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  • 10
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    The combustion process (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The effect of thermodynamic, chemical, and physical properties on the combustion of materials is discussed. The mechanisms which produce and support combustion of various materials are examined. The effects of free radical reactions, convection and gravitational effects on combustion rates, and changes in flame propagation due to size and shape of surfaces are described.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 3-7
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  • 11
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    Electromagnetic compatibility fundamentals applied to spacecraft radio communication systems (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A design guide for minimizing electromagnetic interference in aerospace communication equipment for ground stations is presented. Specifically treated are the mechanisms of generating unwanted radio emissions that may affect station operations as well as other communications services, the mechanisms by which sensitive receivers become susceptible to interference, means for reducing interference, standard methods of measurement, and the problems of site selection. The sources of interference are viewed primarily as originating from communications transmitters aboard spacecraft and aircraft, ground transmitters within and outside the ground stations, and other electrical sources on the ground that are not intended to radiate.
    Keywords: COMMUNICATIONS
    Type: NASA. Goddard Space Flight Center Radio Freq. Interference Handbook; p 1-106
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  • 12
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    Experiment T001: Entry communication on the Gemini 3 mission (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Water addition to the Gemini 3 exhaust plasma was studied to determine its effectiveness in the establishment of communication links during the entry portion of the flight. Attenuation levels were measured with and without water injection at uhf frequencies of 230.4 and 296.8 megahertz and at the C-band frequency of 5690 megahertz. Ultrahigh frequency signals that had been blacked out were restored to significant levels, during early portions of the water-injection sequence, by the high flow rate injection. The C-band signal was enhanced by medium and high flow rate injections during the latter portion of the injection period. The uhf signal recovered during water injection resulted in an antenna pattern that was beamed in the radial direction of injection from the spacecraft. Postflight analysis showed that the uhf recovery data were consistent with injection-penetration theory.
    Keywords: COMMUNICATIONS
    Type: The Gemini Porgram: Phys. Sci. Expt. Sum.; p 471-485
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  • 13
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    Investigations on a cylindrical antenna as a diagnostic probe for isotropic and magnetized plasmas (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Impedance behavior of short cylindrical antenna used as diagnostic probe in isotropic and magnetized plasmas
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 47-56
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  • 14
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    Supersonic cruise inlets (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Design and characteristics of supersonic cruise inlets
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 283-312
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  • 15
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    Conditions for local thermodynamic equilibrium in uranium (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Model for calculation of parameters for local thermodynamic equilibrium in uranium
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: FLORIDA UNIV. RES. ON URANIUM PLASMAS AND THEIR TECHNOL. APPL. 1971; P 173-178
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  • 16
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    Communications control group assembly - Teletype line switching equipment (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Communications control group teletype line switching equipment for space stations
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 113-116
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  • 17
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    Antenna rigging angle optimization within structural member size design optimization (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Antenna rigging angle optimization within structural member design for improved antenna performance
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 81-87
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  • 18
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    Antenna structures - Evaluation of reflector surface distortions (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Reflector surface distortions of 210 ft antenna and their effects on radio frequency performance
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 76-80
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  • 19
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    Tracking and data acquisition elements research - Polarization diverse S band feed cone (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Polarization diverse S band feed cone for DSIF reflector antennas
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 66-72
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  • 20
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    A second/third order hybrid phase locked receiver for tracking Doppler rates (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Second/third order hybrid phase locked receiver for tracking frequency ramp signals
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 42-45
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  • 21
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    Refractivity influence on DSS Doppler data (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Examination of deep space Doppler data for terrestrial media contamination
    Keywords: COMMUNICATIONS
    Type: THE DEEP SPACE NETWORK, VOL. 1 15 FEB. 1971; P 31-41
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  • 22
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    The effects of spatial nonuniformities on high temperature microwave breakdown (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Effects on high temperature microwave antenna breakdown of ionization frequency, collision frequency, diffusion coefficient, and breakdown parameters
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 489-508
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  • 23
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    An automatic antenna impedance matcher for reentry vehicle applications (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Impedance matcher for automatically maximizing power radiated from X band antenna on reentry vehicle by eliminating power dissipated as heat
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 449-463
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  • 24
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    Electromagnetic wave propagation in a lossy plasma slab with a gradient transverse to the incident wave (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Computer solution of plane electromagnetic wave interaction with bounded inhomogeneous plasma slab with electron density gradient transverse to wave
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 427-448
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  • 25
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    Radiation from circumferential slots on plasma-clad cones (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Slot antenna radiation pattern distortion produced by boundary layer plasma sheath around conical reentry vehicles
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 411-425
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  • 26
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    Antenna performance in the presence of a turbulent plasma (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Antenna radiation patterns and electron density profiles in turbulent plasma flow
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 379-410
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  • 27
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    Effects of reentry plasma on RAM C-1 VHF telemetry antennas (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Reentry plasma effects on RAM C-1 VHF telemetry antenna radiation patterns
    Keywords: COMMUNICATIONS
    Type: THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 183-201
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  • 28
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    Shock tube measurement of admittance of RAM C and RAM C-C diagnostic antennas (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Shock tube measurements of admittance of RAM C-2 and RAM C-3 diagnostic antenna admittance to analyze accuracy of calculated electron density
    Keywords: COMMUNICATIONS
    Type: THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 157-182
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  • 29
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    RAM C-3 S-band diagnostic experiment (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: RAM C-3 S band diagnostic antenna systems and calculations of electron density profiles
    Keywords: COMMUNICATIONS
    Type: THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 137-155
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  • 30
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    Thermal design of a satellite telescope (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Thermal control techniques in designing large orbiting telescopes
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA, WASHINGTON OPT. TELESCOPE TECHNOL. 1970; P 359-379
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  • 31
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    Thermodynamics of the internal combustion engine (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Pollution aspects of internal combustion engine thermodynamics
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ET. AND THERMODYN. IN HIGH TEMP. GASES 1970; P 31-40
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  • 32
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    Communications system research (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Coding, synchronization, combinatorial, multiple access, propagation, and permutation studies for telecommunications systems
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 25-89
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  • 33
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    Rocket combustion instability suppression with cavity resonators (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Properly tuned Helmholtz resonator damping devices are an effective method for eliminating high frequency combustion instability in rocket engine thrust chambers. A program was implemented with the objective of extending Helmholtz resonator theory to thrust chamber conditions to establish a standard design procedure. By using systematic cold-flow testing and hot firings, empirical design equations were formulated. An effort is currently underway to extend the design theory to other types of acoustical damping devices such as quarter-wave tubes and slots.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 53-59
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  • 34
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    Pulse performance analysis for small hypergolic propellant rocket engines (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Small rocket engine tests were conducted for the purpose of obtaining pulse performance data to aid in preliminary design and evaluation of attitude control systems. Both monopropellant and hypergolic bipropellant engines of thrust levels from 5 to 445 N (1 to 100 lb) were tested. The performance data for the hypergolic propellant rockets are compared with theoretical performance calculated from idealized chamber filling and evacuation characteristics. Electromechanical delays in valve response and heat transfer characteristics were found to cause substantial deviation between theoretical performance and test performance. The theoretical analysis is modified to obtain a semiempirical model for hypergolic propellant rockets.
    Keywords: PROPULSION SYSTEMS
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 61-74
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  • 35
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    Television experiment (1973)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The fixed and variable Martian features investigated by the TV experiment on Mariner 9 are described. Articles are presented concerning the dust storm of October to November over the Southern Hemisphere; global surface geodesy and cartography; geology; and the satellite astronomy.
    Keywords: COMMUNICATIONS
    Type: Mariner Mars 1971 Proj., Vol. 5; p 63-70
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  • 36
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    Extendible rocket nozzle development (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An evaluation is presented of J-2 engine modifications that will simplify operation and improve reliability of the advanced Saturn 1C launch vehicle. Methods of increasing thrust without extensively modifying the S-2 or S-4B stages are also evaluated. A thrust increase was achieved by raising engine combustion through a redesign of the engine thrust chamber and propellant feed system.
    Keywords: PROPULSION SYSTEMS
    Type: Res. Achievements Rev., Vol. 4, No. 6; p 105-115
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  • 37
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    Reusable surface insulation materials research and development (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Reusable surface insulation is considered a prime candidate for heat shielding large areas of the space shuttle vehicle. The composition and fabrication of RSI materials are discussed, followed by evolution of RSI and current problems, physical and thermal properties, arc plasma test data and results, and material improvement research. Finally, a summary of RSI technology status is presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 373-433
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  • 38
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    Materials and design for ablative heat shields (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The goal of the ablation technology program is to bring ablation research and development to a high state of readiness for application to space shuttle vehicles. Some recent results and current work in the areas of materials, designs, and refurbishment for ablative TPS are reported. Future research and development needs are also presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 505-536
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  • 39
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    Thermal protection system trade studies on ablators and reuseable surface insulation (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Analytical trade studies are presented that consider passive TPS configurations using the following material categories: (1) reuseable surface insulation - surface-coated rigidized ceramic fiber; (2) low density charring ablators; and (3) carbon-carbon and high density ablators for leading edge areas. Emphasized are effects on TPS weight by variations in entry trajectories and material thermal characteristics.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 303-334
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  • 40
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    An assessment of radiative metallic thermal protection systems for space shuttle (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The metallic thermal protection system technology program for the space shuttle is reviewed for the areas of environmental uncertainties, materials data base, TPS design concepts and heat-shield panel configurations, testing and evaluation of materials, panels, and complete systems.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 267-302
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    Velocity diagrams (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The selection and design of velocity diagrams for axial flow turbines are considered. Application is treated in two parts which includes: (1) mean-section diagrams, and (2) radial variation of diagrams. In the first part, the velocity diagrams occurring at the mean section are assumed to represent the average conditions encountered by the turbine. The different types of diagrams, their relation to stage efficiency, and their selection when staging is required are discussed. In the second part, it is shown that in certain cases the mean-section diagrams may or may not represent the average flow conditions for the entire blade span. In the case of relatively low hub- to tip-radius ratios, substantial variations in the velocity diagrams are encountered. The radial variations in flow conditions and their effect on the velocity diagrams are considered.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 1; p 69-99
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  • 42
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    The Goddard helical tape recorder (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A spacecraft recorder was developed with the objective of functioning continuously for 5 years. The resulting design employed a metallic tape wound in a 200-turn helix. A direct drive, brushless dc torquer and servo speed control drove the recorder at 3 rpm for recording and 54 rpm for playback.
    Keywords: COMMUNICATIONS
    Type: 6th Aerospace Mech. Symp.; p 89-93
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  • 43
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    Development of a silicone ablator for high-heat-flux and high-shear-rate condition (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A silicone material was developed which gives suitable ablative protection in the high heat flux, high shear environments encountered in severe reentry applications, such as nose cones for ballistic vehicles and protection of leading edges or other critical areas of a vehicle. In addition, the ease of handling, low application cost, and room temperature cure make such a silicon material suitable nozzles for the large rockets necessary for vehicle launching. The development of this product is traced from the selection of suitable polymers through the choice of fillers and the finalization of filler loadings.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Goddard Space Flight Center Space Simulation; p 725-748
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  • 44
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    Bias and spread in extreme value theory measurements of probability of error (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Extreme value theory is examined to explain the cause of the bias and spread in performance of communications systems characterized by low bit rates and high data reliability requirements, for cases in which underlying noise is Gaussian or perturbed Gaussian. Experimental verification is presented and procedures that minimize these effects are suggested. Even under these conditions, however, extreme value theory test results are not particularly more significant than bit error rate tests.
    Keywords: COMMUNICATIONS
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 58-68
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  • 45
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    Space simulation and rate dependent radiation testing (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An environmental test facility is described which allows in-situ measurements for evaluation of near real time sinergistic effects of combined space environments.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Goddard Space Flight Center Space Simulation; p 453-460
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  • 46
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    Multilayer insulation thermal protection systems technology (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: A summary is presented of the work performed by Marshall Space Flight Center (MSFC) and industry toward the development of flight-type multilayer insulation(MLI) systems. The MSFC MLI program is divided into three large categories: (1) the generation and compilation of MLI composite test data; (2) the analysis, design, and testing of heat flow through MLI applied to ducting, seams, electrical feedthroughs, structural supports, and the tank sidewall; and (3) the development, modification, and utilization of new testing procedures, tanks, and the test facilities. Numerous data have been generated, analyzed, and documented on different MLI composites.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Achievements Rev., Vol.4, No. 2; p 5-52
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  • 47
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    Nozzle exhaust plume backscatter experiment using the JPL Molsink facility (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Qualitative tests were made by injecting water through a rocket nozzle wall, and the droplet trajectories were observed photographically. These tests were conducted for nozzles in which boundary layer flow is significant. The tests indicated that both gases and particulate matter will be found in the region outside of the plume boundaries, and can be calculated using current analytical techniques. A test program is being conducted to measure the distribution of exhaust gases from small nozzles using an electron beam/photomultiplier system and a matrix of quartz crystal microbalances. Calibration tests, using simulated hydrazine exhaust product gas mixtures, were also conducted. The test program and results of the pumping calibration tests with hydrazine (simulated hydrazine exhaust products) are reported.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: JPL Quart. Tech. Rev., Vol. 1, No. 4; p 89-96
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  • 48
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    The use of the Earth-Moon system as a radio tracking facility (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The use of the earth-moon system for radio tracking has several potentially useful aspects, from a scientific standpoint: extension of the baseline by two orders of magnitude, absence of lunar atmosphere, higher-velocity parallax with a longer period, and the moon's more modellable rotation. The facility would be a convenient base station for other research, not directly involving the tracking capability, but utilizing its orbiting data link features.
    Keywords: COMMUNICATIONS
    Type: Proc. of the Conf. on Exptl. Tests of Gravitation Theories; p 249-251
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  • 49
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    Radio tracking with the Deep Space Network (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Range and Doppler measurements for the Mariner 6 and 7 spacecraft are described. The Doppler tracking system and the two systems of spacecraft ranging apparatus being used in the Deep Space Network are illustrated. Charged particle calibration is considered. Equipment characteristics are presented for the ranging apparatus.
    Keywords: COMMUNICATIONS
    Type: Proc. of the Conf. on Exptl. Tests of Gravitation Theories; p 158-165
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  • 50
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    Experiment Do14: Ultrahigh and very high frequency polarization (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The measurement of inhomogeneities in the electron content along the orbital paths of Gemini 8 and Gemini 9 missions was not accomplished because the tracking information was not available. The use of ultrahigh frequency radio transmission was the primary factor in the successful removal of a very high frequency Faraday rotation ambiguity; but, as was expected, this was not very useful for fine-scale polarization studies. Ionosonde data were useful in the computation of the slab thickness at the closest point of approach of the spacecraft.
    Keywords: COMMUNICATIONS
    Type: NASA. Manned Spacecraft Center The Gemini Program: Phys. Sci. Expt. Sum.; p 487-507
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  • 51
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    Considerations on precision temperature control of a large orbiting telescope (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Precision temperature control of large orbiting telescopes
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: OPT. TELESCOPE TECHNOL. 1970; P 417-424
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  • 52
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    Spacecraft telecommunications systems - A digital command system development (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: All digital, single channel command subsystem for spacecraft communication
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 126-129
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  • 53
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    Rate constants from ignition studies of the H2-CO-O2 system (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Rate constant determination for ignition of hydrogen carbon monoxide oxygen system
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ET. AND THERMODYN. IN HIGH TEMP. GASES 1970; P 105-117
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  • 54
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    Applied mechanics (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Spacecraft antenna optimization, receptance coupling program, deformation modes and dynamic response of structures, and holographic measurements
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 171-190
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  • 55
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    Calibration of radar data from Apollo 16 results, part X (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Predictions of surface and near surface blockiness using earth based radar measurements were made. Two polarizations of the radar echoes were measured - polarized and depolarized. Particular attention was given to the depolarized echoes. North Ray and South Ray Craters and a 512-m diameter lunar crater in the Flamsteed Ring were used for the study.
    Keywords: COMMUNICATIONS
    Type: NASA. Lyndon B. Johnson Space Center Apollo 16 Prelim. Sci. Rept.; 3 p
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  • 56
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    Bistatic-radar investigation (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The purpose of the reported experiment was to determine the principal electromagnetic and structural properties of the lunar surface from the observation of command and service module (CSM) radio transmissions that were reflected from the lunar surface and received on earth. These transmissions emanate from the CSM communication systems at wavelengths of 13 cm (S-band) and 116 cm (very high frequency (VHF)). Lunar crustal properties such as dielectric constant, average slope and slope probability, density, small-scale surface roughness, and embedded rocks to a depth of 20 m may be determined. The results are proving to be most useful in understanding the processes that have produced and modified the crust and in distingushing between adjacent and subjacent geological units. The experimental observations are also of intrinsic interest in the study of electromagnetic scattering.
    Keywords: COMMUNICATIONS
    Type: NASA. Lyndon B. Johnson Space Center Apollo 16 Prelim. Sci. Rept.; 13 p
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  • 57
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    Oxidation protected carbon-carbon (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Pyrolized carbon-carbon has one unique advantage over other materials that makes its application to the space shuttle thermal protection system very attractive. This unique characteristic is the increase in material strength and modulus with increase in temperature up to about 2500 K (4040 F). Offsetting this unique advantage are disadvantages which include brittleness, high cost, and the tendency of the material to react with oxygen, particularly at high temperatures. The development of an oxidation inhibitor for the material and the definition of fabrication processes for selected full-scale components are considered.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA Space Shuttle Technol. Conf.; p 335-372
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  • 58
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    Development of materials screening tests for oxygen-enriched environments (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The criteria governing materials to be used in an oxygen enriched atmosphere and tests to determine suitability for fireproof considerations in spacecraft design are discussed. The nine tests applied to materials before acceptance in spacecraft construction are presented. The application of the standard tests to determine ranking of materials is included.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 23-27
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  • 59
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    Electromagnetic compatibility design guideline for STADAN (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Procedures for achieving electromagnetic compatibility in electronic and electrical equipment for aerospace ground stations are investigated. The application of shielding theory to good design is treated and standards of good practice are outlined for bonding, grounding, wiring, and cabling. Some aspects of filter design are explained, and suggestions are given for the application of filters to electronic and electrical equipment.
    Keywords: COMMUNICATIONS
    Type: NASA Goddard Space Flight Center Radio Freq. Interference Handbook; p 107-198
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  • 60
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    Overview of the AF Avionics Laboratory reentry electromagnetics program (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Radio wave propagation through plasmas studied for communication with hypersonic vehicles during reentry
    Keywords: COMMUNICATIONS
    Type: NASA. LANGLEY RES. CENTER THE ENTRY PLASMA SHEATH AND ITS EFFECTS ON SPACE VEHICLE ELECTROMAGNETIC SYSTEMS, VOL. 1 1970; P 3-17
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  • 61
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    Communications elements research (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Components and techniques for radio and optical space communication
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 90-120
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  • 62
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    Spacecraft radio - TOPS radio frequency subsystem (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Radio frequency subsystem requirements and estimated reliability data for Thermoelectric Outer Planet Spacecraft
    Keywords: COMMUNICATIONS
    Type: SPACE PROGRAMS SUM. NO. 37-61, VOL. 3 28 FEB. 1970; P 121-125
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  • 63
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    Realization of the ideas of K. E. Tsiolkovskiy in the reports of the GSRM (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Design and development of rocket engines
    Keywords: PROPULSION SYSTEMS
    Type: TRANS. OF THE FIRST LECTURES DEDICATED TO THE DEVELOP. OF THE SCI. HERITAGE OF K. E. TSIOLKOVSKIY APR. 1970; P 1-10
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  • 64
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    Evolution of a spacecraft antenna system (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Mechanically despun antenna system design for spin stabilized spacecraft used in ATS and Intelsat systems
    Keywords: COMMUNICATIONS
    Type: JPL PROC. OF THE 4TH AEROSPACE MECH. SYMP. 15 JAN. 1970; P 13-18
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  • 65
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    Basic turbine concepts (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Turbine geometric, flow, energy transfer, efficiency, and performance characteristics are considered by the use of definitions, diagrams, and dimensionless parameters. Emphasis is placed on the determination of the fluid velocity as it passes from one blade row to the next. The general methods for constructing velocity diagrams and relating them to the work and flow capacity of the turbine are discussed.
    Keywords: PROPULSION SYSTEMS
    Type: Turbine Design and Appl., Vol. 1; p 21-67
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  • 66
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    Radar augmentation device (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The radar augmentation device (RAD) serves to increase the radar response of a target body and thus expedite radar acquisition. The design and development of the RAD are discussed with particular emphasis on technical problems that were encountered and solved. Discussions of the mode of operation of the RAD and the ground test history are also included.
    Keywords: COMMUNICATIONS
    Type: NASA. Ames Res. Center 6th Aerospace Mech. Symp.; p 65-72
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  • 67
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    Heat pipes for spacecraft temperature control: Their usefulness and limitations (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Heat pipes are used in spacecraft to equalize the temperature of structures and maintain temperature control of electronic components. Information is provided for a designer on: (1) a typical mounting technique, (2) choices available in wick geometries and fluids, (3) tests involved in flight-qualifying the design, and (4) heat pipe limitations. An evaluation of several heat pipe designs showed that the behavior of heat pipes at room temperature does not necessarily correlate with the classic equations used to predict their performance. They are sensitive to such parameters as temperature, fluid inventory, orientation, and noncondensable gases.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: 6th Aerospace Mech. Symp.; p 33-41
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  • 68
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    Magnetospheric radio noise (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Observations, made by the RAE satellite, of earth magnetospheric noise are reported. The observations show radio noise exists at 700 kHz and below. The results are included in graphs.
    Keywords: COMMUNICATIONS
    Type: Significant Accomplishments in Sci., 1970; p 75-80
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  • 69
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    Materials for foam type insulation (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: An internal foam fabrication is one of the concepts being considered for cryogenic insulation on the hydrogen tanks of the shuttle vehicle. The three-dimensional polyurethane used on the S-4 B tanks failed to meet the higher temperature requirements of the shuttle vehicle, however, and other foams under consideration include polyisocyanurates, polyphenylene oxides, polyimides, and polybenzimidazoles. Improved adhesive systems for attaching the foams to the interior tank wall are under study.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Cryog. Res. at MSFC: Res. Achievements Rev., Vol. 4, No. 2; p 179-184
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  • 70
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    A review of the Grumman orbiter wind tunnel heat transfer tests (1972)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: Tests were conducted in the NASA Langley continuous flow, variable density and Mach 20 helium tunnels. The orbiter was tested alone and with various side and tandem mounted tanks. Test conditions spanned a Reynolds number range which resulted in both laminar and turbulent flows. Experimental studies also examined the heat transfer problems associated with integration of the auxiliary propulsion system into the orbiter. Tests in the hypersonic shock tunnel investigated heating to cavities and heating from single and multiple hydrogen-oxygen plumes while tests, run as part of the configuration evaluation, examined the heating to wing pods.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 297-345
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  • 71
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    Flammability tests for Apollo command module and lunar module mockup (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The flammability test program for Apollo command module and lunar module mockups is described. The fire safety design of the modules was verified by performing deliberate ignitions at many locations while the interior atmosphere was controlled to simulate realistic flight conditions. The data obtained for each test and restrictions on various materials are discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 43-54
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  • 72
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    Manned spacecraft nonmetallic-materials flammability selection criteria and requirements (1971)
    In:  CASI
    Details
    Publication Date: 2005-11-30
    Description: The criteria and requirements governing the selection and use of nonmetallic materials in manned spacecraft to control potential fire hazards are reviewed. The development of flammability requirements is discussed and traced through the historical evolution. Events that dictated the changes that have taken place are discussed. The current nonmetallic material requirements are presented. Significant features of a nonmetallic materials handbook are included.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Conf. on Mater. for Improved Fire Safety; p 9-21
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  • 73
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    Development of Tsiolkovskiy's ideas on the use of air in the engines of space vehicles (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Atmospheric air storage for use in space vehicle engines during planetary flight
    Keywords: PROPULSION SYSTEMS
    Type: TRANS. OF THE FIRST LECTURES DEDICATED TO THE DEVELOP. OF THE SCI. HERITAGE OF K. E. TSIOLKOVSKIY APR. 1970; P 69-76
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  • 74
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    Prediction of heat-transfer characteristics for ejector exhaust nozzles (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Heat balance equation for predicting heat transfer of ejector exhaust nozzle at afterburning phase
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: L. METHODS IN AIRCRAFT AERODYN. 1970; P 623-638
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  • 75
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    Heat-transfer testing procedures in phase B shuttle studies with emphasis on phase change data improvement (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The procedures used in the application of the phase change technique to the phase B shuttle configuration are discussed along with factors which may affect data accuracy. These factors include variation of thermal properties of phase change model material, sensitivity of measured heat transfer coefficients to the assumed value of the adiabatic to total temperature ratio, and wall temperature effects. These sensitivities are illustrated in sample calculations for a shuttle geometry. Factors which may affect the visual clarity and interpretation of phase change data are discussed, and a method of improving photographic data quality through the use of polarized light is presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 661-682
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    An analysis of the booster plume impingement environment during the space shuttle nominal staging maneuver (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: An experimental study of the plume impingement heating on the space shuttle booster afterbody resulting from the space shuttle orbiter engine plumes was conducted. The 1/100-scale model tests consisted of one and two orbiter engine firings on a flat plate, a flat plate with a fin, and a cylinder model. The plume impingement heating rates on these surfaces were measured using thin film heat transfer gages. Results indicate the engine simulation is a reasonable approximation to the two engine configuration, but more tests are needed to verify the plume model of the main engine configuration. For impingment, results show models experienced laminar boundary layer convective heating. Therefore, tests at higher Reynolds numbers are needed to determine impingment heating.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 607-644
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  • 77
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    Determination of aerothermodynamic environment uncertainties with application to space shuttle vehicles (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: In an effort to minimize the cost of the thermal protection system (TPS) for space shuttles, an analysis is made of environmental uncertainties. The basic categories of these uncertainties include aerodynamic heating, trajectory dispersions, atmospheric variations, and vehicle attitude variations. Also discussed are TPS design sensitivity to environmental uncertainties, and uncertainty profiles. Preliminary results indicate moderate TPS cost for a high confidence level environment may be obtained.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA. Langley Res. Center Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 503-518
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    Aerothermodynamic measurements for space shuttle configuration in hypersonic wind tunnels (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The effect of shuttle configuration geometry, angle of attack, and free stream flow conditions on the heat-transfer distribution as influenced by three-dimensional effects, the wing-fuselage shock-interaction, and resultant wing-impingement phenomena are examined. In addition, the data provided information regarding the flow field in the vicinity of the nose and boundary layer transition in the plane of symmetry of the fuselage. The data included measurements of the surface pressure, the heat transfer rate distributions, (using models instrumented with thermocouples and models painted with thermographic phosphor) and schlieren and shadowgraph photographs. Posttest photographs of the painted models supplemented the heat transfer data.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 469-501
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  • 79
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    Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 2: Studies of lee-surface heating at hypersonic Mach numbers (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: Lee surface heating data, obtained at relatively low unit Reynolds numbers at Mach 6 and 19, are discussed with emphasis on the peak heating behavior. Surface pressures measured along the lee meridian of the delta-wing orbiter are presented and analyzed in conjunction with the heating. The effects of nose bluntness and lee surface geometry on the heating are discussed and general guidelines are presented for modifying the lee surface geometry of the shuttle to reduce vortex-induced heating. The application of the wind tunnel results to realistic shuttle flight conditions is discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 451-467
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  • 80
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    Effects of roughness on heating and boundary-layer transition. Part 2: effects of discrete roughness on heating (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: A preliminary investigation on the effects of roughness on heating in delta wing orbiters was conducted on the windward surface of the vehicle. The purpose of the experiment was to determine the feasibility of using parametric relationships obtained from discrete roughness effects on heating in flat plates and cones, to complex shuttle configurations. An attempt was also made to characterize what parameters were needed to influence roughness. Experimental results show that effective roughness Reynolds numbers are less than or equal to those of flat plates at the same edge Mach number, but, the roughness correlations for plates and cones cannot be applied to the shuttle configuration.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 395-411
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  • 81
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    Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 1: Flow separation and flow field viscous phenomena of a delta-wing shuttle orbiter configuration (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: Results of a pitot pressure investigation of the flow field on the lee side of a delta wing shuttle orbiter are presented. The results delineate the extent of the lee side separated flow and give a tentative cross sectional definition to the shock wave structure for angles of attack of 15 deg and 30 deg. It is shown that while, in general, the effects of Reynolds number on the flow field are not large, detailed effects are observed that may have significant bearing on the heating estimate. Two examples are cited for an angle of attack of 15 deg; these are: (1) The scope of the vertical tail exposed to the unseparated flow increases with increasing Reynolds number and (2) the depth of the separated flow adjacent ot where the bow wave crosses the wing appears to decrease with increasing Reynolds number. In addition, it is shown that at a spanwise station outboard of the wing-fuselage juncture, increasing Reynolds number decreased the pitot pressure in the unseparated flow. This defect of pitot pressure appears associated with the flow over the wing-fillet-fuselage juncture.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 413-449
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  • 82
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    Effects of roughness on heating and boundary-layer transition. Part 1: Effects of simulated panel joints on boundary-layer transition (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The effects of distributed roughness, arising from space shuttle orbiter panel joints, on boundary layer transition are investigated. The North American Rockwell 134B delta wing shuttle configuration was used for the study. Results show: (1) Premature boundary layer transition occurred in models having simulated heat shield panels with rased joints. (2) Laminar flow was maintained with slot type panel joint models to a Reynolds number twice that at which transition occurred in raised joints. (3) Significant increases in peak surface temperature and the time during which turbulent flow occurs may result from distributed roughness of heat shield panel joints. (4) Laminar and turbulent heating levels were predicted within available theories. (5) A complex interference between the wing and fuselage flow was observed in the delta wing model.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 375-394
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  • 83
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    High Reynolds number turbulent heating to two simplified shuttle configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: Turbulent heating and transition data, taken from three test facilities, for two space shuttle configurations are presented. Major efforts were on: (1) the effect of the two geometries having different amounts of cross flow and how the different cross flows affect heating and transition, (2) the experimental level of turbulent heating and the ability to predict the level of turbulent heating, and (3) a comparison of the transitional and turbulent heating in three facilities with two model scale sizes to investigate the facility effects and scale-size effect on transition and turbulent heating. The three facilities in which the configurations were tested are the Langley Mach 8 variable-density hypersonic tunnel and the Arnold Engineering Development Center tunnel B and tunnel F at Mach numbers of 8 and 10.5, respectively.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 347-373
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  • 84
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    Experimental and theoretical aerodynamic heating and flow field analysis of a space shuttle orbiter (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The results of work on the McDonnell Douglas delta wing orbiter are summarized and compared to other data and theories where applicable. The tests were conducted in the continuous hypersonic Tunnel B at Mach 8 and in the hypervelocity hotshot Tunnel F at Mach 10.5. Photographic data are used to illustrate the regions of peak heating on the lee-side and to show the vortical nature of the flow. Windward centerline data include measurements of shock angle, surface pressure, flow field pitot pressure and total temperature, and heat transfer rate coefficient distributions. Shock angles, surface pressures, and local Mach number distributions are compared with tangent cone theory over an angle of attack range from 10 to 60 deg. The measured heat transfer rate coefficient distributions are compared to both laminar and turbulent theories and boundary layer transition data are compared to the McDonnell Douglas criteria.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 261-296
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  • 85
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    Structure of proton centers and associated nonthermal bursts at microwave frequencies (1973)
    In:  CASI
    Details
    Publication Date: 2006-04-05
    Description: A very broad band of electromagnetic radiation is emitted during solar flares, especially at the explosive phase. The existence of a large variety of plasmas with various densities and a wide range of temperatures or energies is proposed as the initiating agent. The manner in which the plasmas are heated and accelerated to subrelativistic and relativistic energies is discussed. Observational evidence on the characteristics of active regions which produced proton flares and on the structure of the associated nonthermal microwave bursts of the sun is presented. The behavior of subrelativistic electrons on the sun is described.
    Keywords: COMMUNICATIONS
    Type: NASA, Washington High Energy Phenomena on the Sun; p 78-86
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  • 86
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    Investigation of the possibility of use of vibroacoustical signals for purposes of diagnostics in aeronautical engineering (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The application of vibroacoustic techniques for diagnosing aircraft engine malfunctions is discussed. An experiment was conducted to determine the defects introduced by the nature of change in the amplitude-frequency characteristics of the noises and vibrations of an aircraft jet engine. The manner in which the defects were simulated is explained. The test equipment used during the experiment is identified. The results of the amplitude-frequency characteristics investigation are summarized to show optimum location of the microphone pick-up to record the acoustic data.
    Keywords: PROPULSION SYSTEMS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 317-319
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  • 87
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    Vibration resistance of the wire-feed mechanism of a magnetic recording apparatus (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The effects of external mechanical and climatic actions on the efficient operation of magnetic tape recording equipment are analyzed. The efficiency and reliability of the recording system are determined by the structural parameters and the characteristics of the individual elements of the transport mechanism circuit. The resistance of tape recording equipment to the effects of vibration is considered essential for reliable operations. Methods for insuring reliable tape transport and recording action are discussed.
    Keywords: COMMUNICATIONS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 271-274
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  • 88
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    Measurement of irregularities in angular velocities of rotating assemblies in memory devices on magnetic carriers (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: Problems in measurement of irregularities in angular velocity of rotating assemblies in memory devices with rigid and flexible magnetic data carriers are discussed. A device and method for determination of change in angular velocities in various frequency and rotation rate ranges are examined. A schematic diagram of a photoelectric sensor for recording the signal pulses is provided. Mathematical models are developed to show the amount of error which can result from misalignment of the test equipment.
    Keywords: COMMUNICATIONS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 279-282
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  • 89
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    The problem of carrying out a diagnosis of an internal combustion engine by vibroacoustical parameters (1973)
    In:  CASI
    Details
    Publication Date: 2006-03-28
    Description: The physics of noise formation in an internal combustion engine is discussed. A dependence of the acoustical radiation on the engine operating process, its construction, and operational parameters, as well as on the degree of wear on its parts, has been established. An example of tests conducted on an internal combustion engine is provided. A system for cybernetic diagnostics for internal combustion engines by vibroacoustical parameters is diagrammed.
    Keywords: PROPULSION SYSTEMS
    Type: Cybernetic Diagnostics of Mech. Systems with Vibro-acoustic Phenomena (NASA-TT-F-14899); p 247-249
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  • 90
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    Error analysis of bent ray radio occultation measurments (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-12
    Description: There are two types of experimental measurement errors of the Doppler data associated with the radio occultation, random and systematic. Random errors are due to thermal noise in the transmission channel, and the phase lock loop, and quantization error in the digital circuitry. These are called noise type errors. The systematic errors are due to geometric uncertainty and equipment phase instability. Considered is the amount of uncertainty, due to random measurement errors, in the refractivity profiles reconstructed by this type of indirect sensing experiment. A class of refractivity profiles is defined which approximately fit the set of measured data. Bounds are placed on the extent of this class of solution profiles. To accomplish this, the sensivity of the reconstructed refractivity profiles to errors in the measured quantity and the statistics of the errors in the measurement are examined.
    Keywords: COMMUNICATIONS
    Type: NASA. Ames Res. Center Math. of Profile Inversion; 5 p
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  • 91
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    Some special cases of the electromagnetic inverse problem (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-12
    Description: A review of exact techniques for determining the surface of a three-dimensional perfectly conducting body is given, followed by some new results on the uniqueness question concerning the number of measurements that may be required to explicitly determine the surface of the body. It is then shown that the inhomogeneous but spherically symmetric dielectric electromagnetic case is reducible to a scalar inverse problem that can be treated by known techniques.
    Keywords: COMMUNICATIONS
    Type: NASA. Ames Res. Center Math. of Profile Inversion; 11 p
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  • 92
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    A new look at AP/composite propellant combustion (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Some theoretical studies on the time-independent and oscillatory combustion of nonmetallized ammonium perchlorate (AP)/composite propellants are presented. A coherent and unified interpretation was made of the voluminous data available from experiments related to propellant combustion. Three fundamental hypotheses are introduced: the extent of propellant degradation at the vaporization step has to be specified through a scientific criterion; the condensed-phase degradation reaction of ammonium perchlorate to a vaporizable state is the overall rate-limiting step; gas-phase combustion rate is controlled by the mixing rate of fuel and oxidizer vapors. In the treatment of oscillatory combustion, the assumption of quasi-steady fluctuations in the gas phase is used to supplement these hypotheses.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: JPL JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-77
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  • 93
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    Minimum impulse tests of 0.45-N liquid hydrazine catalytic thrusters (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: An exploratory test series was conducted on three types of 0.45-N (0.1 lbf) liquid hydrazine thrusters to ascertain the minimum impulse bit capability for this class of engine. The test series is described and the results are presented. The testing was performed at 21 and 145 C (70 and 300 F) while maintaining nominal 0.45 N (0.1 lbf) upstream conditions. Valve on-times as low as 0.008 sec were applied. Impulse bits were observed for thruster temperatures of 21 and 145 C (70 and 300 F), respectively.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 107-112
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  • 94
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    Spacecraft ion beam noise effects (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: An estimate of the antenna noise temperature and the uplink signal-to-noise ratio has been made for Bremsstrahlung radiation emitted by a spacecraft ion beam; a worst-case situation in which the spacecraft antenna is located in the exit plane of the ion beam and directed at varying angles into the ion beam is assumed. Numerical results of the antenna noise temperature versus antenna pointing angle are given for a typical set of ion beam and antenna pattern parameters. The uplink signal-to-noise ratio due to the ion beam noise alone is given in terms of a critical range in AU at which a typical ranging transmission is received with S/N = 0 db. The effects of the ion beam divergence angle and antenna distance on the ion beam are also presented. Results of the study show typical increases in the antenna noise temperature of about 0.2 K and critical ranges of the order of 3-5 AU. An ion engine thus generally introduces an undetectable level of noise into a spacecraft receiver.
    Keywords: COMMUNICATIONS
    Type: JPL Quart. Tech. Rev., Vol. 2, No. 2; p 61-71
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  • 95
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    Interplex: An analysis of optimized power allocations for two and three channel PSK/PM telecommunications systems (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Optimal design concepts are presented for two- and three-channel telemetry modes in the context of the Mariner Venus-Mercury 1973 mission and the usefulness of interplex modulation techniques is discussed. These ideas are applied as an example to one Mariner Venus-Mercury 1973 telemetry mode to demonstrate that interplex can reduce the required total average power by more than 2 dB in some cases.
    Keywords: COMMUNICATIONS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 143-151
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  • 96
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    Mariner 9 propulsion subsystem performance during interplanetary cruise and Mars orbit insertion (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: On 14 November 1971 the Mariner 9 1334-N-(300-lbf)-thrust rocket engine was fired for just over 15 min to place the first man-made satellite into orbit about Mars. Propulsion subsystem data gathered during the 5-month interplanetary cruise and orbit insertion are of significance to future missions of this type. Specific results related to performance predictability, zero g heat transfer, and nitrogen permeation, diffusion, and solubility values are presented.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 113-122
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  • 97
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    Analysis of the failure of a polyester peripheral drive belt on the Mariner Mars 1971 flight tape recorder (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: A peripheral drive belt on the Mariner Mars 1971 tape recorder failed when a thin longitudinal strip separated off one edge. Analysis showed that the most probable cause of failure occurred from flexural fatigue initiating in mechanically weak locations which are introduced into the belt during fabrication. Methyl ethyl ketone, which is employed as a cleaning solvent during fabrication, was found to cause permanent reduction in engineering properties of polyester and could have contributed to the reduction of the fatigue resistance. Fatigue properties of the polyester drive belt are reviewed for the operating condition, as well as the sensitivity of polyester to cleaning solvents and the origin of mechanically weak locations.
    Keywords: COMMUNICATIONS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1; p 82-99
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  • 98
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    Development of propulsion for high atmospheric pressure or dense environments (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: The development of a propulsion system that employs a detonating propellant is described, and the need for such a system and its use in certain planetary atmospheres are demonstrated. A theoretical formulation of the relevant gas-dynamic processes was developed, and a related series of experimental tests were pursued.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-52
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  • 99
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    Small rocket exhaust plume data (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: During recent cryodeposit tests with an 0.18-N thruster, the mass flux in the plume back field was measured for the first time for nitrogen, carbon dioxide, and a mixture of nitrogen, hydrogen, and ammonia at various inlet pressures. This mixture simulated gases that would be generated by a hydrazine plenum attitude propulsion system. The measurements furnish a base upon which to build a mathematical model of plume back flow that will be used in predicting the mass distribution in the boundary region of other plumes. The results are analyzed and compared with existing analytical predictions.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: JPL Quart. Tech. Rev., Vol. 2, No. 2; p 90-99
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  • 100
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    Studies on the frictional behavior of magnetic recording tapes (1972)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Methods were developed for measuring frictional forces acting on a magnetic tape in motion or at rest, as well as the extent of stick slip. The effects of factors such as temperature, humidity, kind of gaseous atmosphere, and tape speed on the frictional interaction between various tapes and heads were investigated. Results were instrumental in the selection of a tape for the Mariner Mars 1971 spacecraft. Studies are reported on the stick slip behavior of tapes and the performance of a metallic tape, compared with the usual plastic tapes.
    Keywords: COMMUNICATIONS
    Type: JPL Quarterly Tech. Rev., Vol. 2, No. 1.; p 100-106
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