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  • Other Sources  (16)
  • SPACECRAFT PROPULSION AND POWER  (8)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (4)
  • ELECTRONICS AND ELECTRICAL ENGINEERING  (4)
  • Life and Medical Sciences
  • 1985-1989  (16)
  • 1960-1964
  • 1
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    Helicopter-V/STOL dynamic wind and turbulence design methodology (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Aircraft and helicopter accidents due to severe dynamic wind and turbulence continue to present challenging design problems. The development of the current set of design analysis tools for a aircraft wind and turbulence design began in the 1940's and 1950's. The areas of helicopter dynamic wind and turbulence modeling and vehicle response to severe dynamic wind inputs (microburst type phenomena) during takeoff and landing remain as major unsolved design problems from a lack of both environmental data and computational methodology. The development of helicopter and V/STOL dynamic wind and turbulence response computation methology is reviewed, the current state of the design art in industry is outlined, and comments on design methodology are made which may serve to improve future flight vehicle design.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Research Center Wind Shear(Turbulence Inputs to Flight Simulation and Systems Certification; p 209-216
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Liquid metal cooled reactors for space power applications (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The technology basis for evaluation of liquid metal cooled space reactors is summarized. Requirements for space nuclear power which are relevant to selection of the reactor subsystem are then reviewed. The attributes of liquid metal cooled reactors are considered in relation to these requirements in the areas of liquid metal properties, neutron spectrum characteristics, and fuel form. Key features of typical reactor designs are illustrated. It is concluded that liquid metal cooled fast spectrum reactors provide a high confidence, flexible option for meeting requirements for SP-100 and beyond.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Oxygen/hydrocarbon combustion devices technology (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A program was conducted to investigate ignition, combustion and heat transfer characteristics of liquid oxygen and RP-1 fuel applicable to large gas generator cycle booster engines. The program was part of a broad effort intended to generate a combustion devices technology base for both RP-1 and methane fuels and both gas generator and staged combustion engine cycles. Two gas generator injector designs were tested over a chamber pressure range of 1500 to 3100 psia and a gas temperature range of 1500 to 2300 R. Both configurations were evaluated for combustion efficiency, gas temperature profile and combustion stability. Thrust chamber firings were conducted using a platelet type main injector and a water cooled calorimeter combustion chamber. Test conditions ranged from 1700 to 2200 psia chamber pressure and from 2.0 to 2.8 mixture ratio. A program goal to reduce previously measured nozzle heating rates was achieved, but at the expense of combustion efficiency.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Johns Hopkins Univ. The 1985 JANNAF Propulsion Meeting, Volume 1; p 271-280
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    LH2 on-orbit storage tank support trunnion design and verification (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A detailed fatigue analysis was conducted to provide verification of the trunnion design in the reusable Cryogenic Fluid Management Facility for Shuttle flights and to assess the performance capability of the trunnion E-glass/S-glass epoxy composite material. Basic material property data at ambient and liquid hydrogen temperatures support the adequacy of the epoxy composite for seven-mission requirement. Testing of trunnions fabricated to the flight design has verified adequate strength and fatigue properties of the design to meet the requirements of seven Shuttle flights.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Application of digital/electric systems to advanced technology aircraft (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Potential improvements in weight and performance of the digital/electric airplane of the 1990s are investigated, using data based on the Integrated Digital/Electric Airplane (IDEA) study, a nine-month investigation of integrated digital/electric concepts. A baseline configuration was compared to these IDEA configurations in terms of economic performance, fuel efficiency, and significant system and aircraft configuration characteristics. The 1990 baseline configuration represents a six to eight percent performance improvement over current technology; however, the IDEA airplane shows an additional three percent improvement in fuel burn performance. This improvement is due to a reduction of over 3000 pounds in systems weight alone.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAWE PAPER 1639
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Design and development of a multibeam 1.4 GHz pushbroom microwave radiometer (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design and operation of a multiple beam, digital signal processing radiometer are discussed. The discussion includes a brief description of each major subsystem and an overall explanation of the hardware requirements and operation. A series of flight tests was conducted in which sea-truth sites, as well as an existing radiometer were used to verify the Pushbroom Radiometer performance. The results of these tests indicate that the Pushbroom Radiometer did meet the sensitivity design goal of 1.0 kelvin, and exceeded the accuracy requirement of 2.0 kelvin. Additional performance characteristics and test results are also presented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA-TM-89005 , NAS 1.15:89005
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Orbital spacecraft resupply technology (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The resupplying of orbital spacecraft using the Space Shuttle, Orbital Maneuvering Vehicle, Orbital Transfer Vehicle or a depot supply at a Space Station is studied. The governing factor in fluid resupply designs is the system size with respect to fluid resupply quantities. Spacecraft propellant management for tankage via diaphragm or surface tension configurations is examined. The capabilities, operation, and application of adiabatic ullage compression, ullage exchange, vent/fill/repressurize, and drain/vent/no-vent fill/repressurize, which are proposed transfer methods for spacecraft utilizing tankage configurations, are described. Selection of the appropriate resupply method is dependent on the spacecraft design features. Hydrazine adiabatic compression/detonation, liquid-free vapor venting to prevent freezing, and a method for no-vent liquid filling are analyzed. Various procedures for accurate measurements of propellant mass in low gravity are evaluated; a system of flowmeters with a PVT system was selected as the pressurant solubility and quantity gaging technique. Monopropellant and bipropellant orbital spacecraft consumable resupply system tanks which resupply 3000 lb of hydrazine and 7000 lb of MMH/NTO to spacecraft on orbit are presented.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: AIAA PAPER 86-1604
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Systems study for an Integrated Digital-Electric Aircraft (IDEA) (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of the Integrated Digital/Electric Aircraft (IDEA) Study are presented. Airplanes with advanced systems were, defined and evaluated, as a means of identifying potential high payoff research tasks. A baseline airplane was defined for comparison, typical of a 1990's airplane with advanced active controls, propulsion, aerodynamics, and structures technology. Trade studies led to definition of an IDEA airplane, with extensive digital systems and electric secondary power distribution. This airplane showed an improvement of 3% in fuel use and 1.8% in DOC relative to the baseline configuration. An alternate configuration, an advanced technology turboprop, was also evaluated, with greater improvement supported by digital electric systems. Recommended research programs were defined for high risk, high payoff areas appropriate for implementation under NASA leadership.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-3840 , NAS 1.26:3840 , D6-52147
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    The investigation of inlet/nozzle flowfield coupling using compact propulsion simulators (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An investigation of airframe/propulsion system flowfield coupling has been conducted in the Ames 11-Foot Transonic Wind Tunnel at Mach numbers from 0.40 to 1.40 and at angles-of-attack from -2 to +20 deg. Propulsive flows were simulated by flow-through, jet-effects, and turbo-powered simulators (CMAPS) techniques. The configuration was a 10 percent scale model of a VSTOL canard/wing fighter configuration with twin podded engine nacelles and nonaxisymmetric nozzles. Localized flowfield interactions were present and inlet-nozzle flowfield coupling was identified at supersonic flight conditions. The configuration with simultaneous inlet and nozzle flow simulation (CMAPS) exhibited lower drag supersonically than the flow-through/jet-effects configuration. During this first wind tunnel application of twin simulators in a full aircraft configuration, the CMAPS and control system proved to be a flexible, reliable testing method.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 85-1284
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Recent developments on a 128 x 128 indium antimonide/FET switch hybrid imager for low-background applications (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: By combining high-quality mesa photovoltaic indium antimonide detector material with a silicon x-y FET switch multiplexer, a useful infrared area detector has been developed. This device is intended for low-background applications, where high sensitivity is required. Initial characterization of the detector at 80 K showed a KTC limited read noise of less than 1000 electrons, good dark current, responsivity uniformity, and a maximum readout rate of 10 MHz. The hybrid mating technology has sufficient precision to allow expansion to a 256 x 256 format. The dark current in the detector material is sufficiently low to allow full-frame integration, even with arrays as large as 256 x 256 elements.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Infrared detectors, sensors, and focal plane arrays; Aug. 21, 22, 1986; San Diego, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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