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  • 1
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    Advanced Propfan Engine Technology (APET) definition study, single and counter-rotation gearbox/pitch change mechanism design (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Single-rotation propfan-powered regional transport aircraft were studied to identify key technology development issues and programs. The need for improved thrust specific fuel consumption to reduce fuel burned and aircraft direct operating cost is the dominant factor. Typical cycle trends for minimizing fuel consumption are reviewed, and two 10,000 shp class engine configurations for propfan propulsion systems for the 1990's are presented. Recommended engine configurations are both three-spool design with dual spool compressors and free power turbines. The benefits of these new propulsion system concepts were evaluated using an advanced airframe, and results are compared for single-rotation propfan and turbofan advanced technology propulsion systems. The single-rotation gearbox is compared to a similar design with current technology to establish the benefits of the advanced gearbox technology. The conceptual design of the advanced pitch change mechanism identified a high pressure hydraulic system that is superior to the other contenders and completely external to the gearboxes.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-168115 , NAS 1.26:168115 , EDR-11283
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The design of an omnidirectional antenna system for the Apollo spacecraft (1964)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Omnidirectional radio antenna system design for Apollo command module
    Keywords: COMMUNICATIONS
    Type: NASA-CR-65178
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced propfan engine characteristics and technology needs (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A comparative study is presented for two of the advanced gas turbine engine designs developed in the course of a proprietary research effort for the NASA Advanced Propfan Engine Technology research program. In these engines, a cycle pressure ratio of 32.5:1 and a 2500 F maximum turbine temperature provide fuel efficient operation in the 32,000-ft altitude, Mach 0.72 cruise speed regime stipulated. Both of the engine configurations incorporate three spools, of which the compressors are dual-spool and the power turbines are free. A major design challenge for axial compressors in the 10,000-shp class was the maintenance of adequate blade heights in the later stages.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1155
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Advanced propfan drive system characteristics and technology needs (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Characteristics of a single-rotation drive system for an advanced turboprop engine are described. The gearbox is designed for a 10,000 shp three-spool, free-turbine engine and is installed in a wing-mounted nacelle. An offset gearbox from an earlier APET study provided the background for the preliminary design and benefit analysis for a 1990s advanced technology versus 1980s state-of-the-art gearbox. High efficiencies were achieved for both designs with inherently high life goals. Increases in design allowables for gears, bearings, and lubricants resulted in improvements for the 1990s design.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 84-1194
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Pollution Reduction Technology Program, Turboprop Engines, Phase 1 (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Exhaust pollutant emissions were measured from a 501-D22A turboprop engine combustor and three low emission combustor types -- reverse flow, prechamber, and staged fuel, operating over a fuel-air ratio range of .0096 to .020. The EPAP LTO cycle data were obtained for a total of nineteen configurations. Hydrocarbon emissions were reduced from 15.0 to .3 lb/1000 Hp-Hr/cycle, CO from 31.5 to 4.6 lb/1000 Hp-Hr/cycle with an increase in NOx of 17 percent, which is still 25% below the program goal. The smoke number was reduced from 59 to 17. Emissions given here are for the reverse flow Mod. IV combustor which is the best candidate for further development into eventual use with the 501-D22A turboprop engine. Even lower emissions were obtained with the advanced technology combustors.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-135040 , EDR-8708
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Two-Dimensional Imaging of OH in a Lean Burning High Pressure Combustor (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Planar laser-induced fluorescence (PLIF) images of OH have been obtained from an optically accessible, lean burning high pressure combustor burning Jet-A fuel. These images were obtained using various laser excitation lines of the OH A (reverse arrow) X (1,0) band for several fuel injector configurations with pressures ranging from 1013 kPa (10 atm) to 1419 kPa (14 atm). Non-uniformities in the combusting flow, attributed to differences in fuel injector configuration, are revealed by these images. Contributions attributable to fluorescent aromatic hydrocarbons and complex fuel chemistries are also not evident.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-106854 , E-9444 , NAS 1.15:106854 , AIAA PAPER 95-0173 , Aerospace Sciences Meeting and Exhibit; Jan 09, 1995 - Jan 12, 1995; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A new method for satellite orbit determination using an operational worldwide transponder network (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The method utilizes computer programs developed for the forthcoming ATS-F/NIMBUS-F tracking and data relay experiment where the basic tracking measurements are multiple path round-trip propagation times and rates. This method of orbit computation has recently been successfully evaluated by tracking a geostationary satellite (ATS-3) using an existing VHF (150 MHz) network of automatic transponders. A master station sequentially interrogates each transponder via the ATS-3. The master site is located at Schenectady, N. Y. and four automatic transponders were located at Shannon, Reykajavik, Buenos Aires, and Seattle respectively. Data at hourly intervals were collected during a 24 hour period on April 18-19, 1973. After correcting this data for known systematic errors it was provided as input to an orbit determination program where all satellite motions during signal propagation are rigorously accounted for. The resulting estimated ATS-3 orbit yielded observational residuals on the order of 100 meters. By using more than one satellite the present scheme is further capable of accurately locating several stationary or mobile terminals as part of the overall orbital solution.
    Keywords: COMMUNICATIONS
    Type: NASA-TM-X-70587 , X-591-74-2 , American Geophysical Union Fall Annual Meeting; Dec 10, 1973 - Dec 13, 1973; San Francisco
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Initial observations of VLF electric and magnetic fields with the Injun 5 satellite (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Very low frequency electric and magnetic field observations by Injun 5 satellite
    Keywords: COMMUNICATIONS
    Type: NASA-CR-101677 , REPT-69-19
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Results of an experiment to locate and read data from unmanned transponders using satellites (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: ATS 1 and 3 satellite VHF transponders for ships and aircraft location, communication and remote sensing, discussing performance test results
    Keywords: COMMUNICATIONS
    Type: NATIONAL TELEMETERING CONFERENCE; Apr 12, 1971 - Apr 15, 1971; WASHINGTON, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Experimental investigation of aeronautical and maritime communications and surveillance using satellites (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The experimental program described included an evaluation of every significant factor affecting the accuracy of position fixing by range measurements from geostationary satellites. The tone-code ranging technique was found to provide a precision of roughly 0.1 n mi at mid-lattitudes with one range measurement at L-band and one at VHF. The factors which introduce bias errors were studied analytically and experimentally, and means of rectifying the bias errors were developed. An operational system at L-band may be expected to provide position fix accuracy of 0.1 n mi over large regions of the earth. The ranging technique developed within this program is digital, and uses a single signalling waveform and a single modem for communications and ranging.
    Keywords: COMMUNICATIONS
    Type: International Astronautical Congress; Oct 07, 1973 - Oct 13, 1973; Baku; Azerbaidzhan SSR
    Format: text
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    NASA TECHNICAL REPORTS
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