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  • 1
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    Overview of Langley systems studies (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Late in 1990, the NASA Systems Integration Group began functioning and the aircraft systems studies entered a second phase. This group proposed tightly coordinated Ames/Langley/Lewis/industry studies that would address a series of tasks to evaluate progress, recommend appropriate direction, and emphasize changes in technology elements based on system level payoffs and potential success assessments. Based on technical and economic assessment studies of the High Speed Civil Transport (HSCT) to date, Mach 2.4 was chosen as the primary focus for the High Speed Research Program with Mach numbers 2.0 and 1.6 being backups in case of technology shortfalls. Langley has established an interdisciplinary team to strengthen the multidisciplinary aspects of aircraft design and analysis. The vehicle focus of this team is the HSCT. At Langley, early HSCT studies focused on turbojet powered aircraft. They also concluded that variable sweep wing concepts require 50/50 subsonic/supersonic to payoff for Mach 3.0 concept. Progress has been good in low sonic boom concepts.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: First Annual High-Speed Research Workshop, Part 1; p 423-455
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Wind-tunnel Investigation of the Air Load Distribution on Two Combinations of Lifting Surface and Fuselage (1947)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-1295
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Method and device for determining bond separation strength using induction heating (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An induction heating device includes an induction heating gun which includes a housing, a U-shaped pole piece having two spaced apart opposite ends defining a gap there between, the U-shaped pole piece being mounted in one end of the housing, and a tank circuit including an induction coil wrapped around the pole piece and a capacitor connected to the induction coil. A power source is connected to the tank circuit. A pull test machine is provided having a stationary chuck and a movable chuck, the two chucks holding two test pieces bonded together at a bond region. The heating gun is mounted on the pull test machine in close proximity to the bond region of the two test pieces, whereby when the tank circuit is energized, the two test pieces are heated by induction heating while a tension load is applied to the two test pieces by the pull test machine to determine separation strength of the bond region.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Induction heating coupler and annealer (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An induction heating device includes a handle having a hollow interior and two opposite ends, a wrist connected to one end of the handle, a U-shaped pole piece having- two spaced apart ends, a tank circuit including an induction coil wrapped around the pole piece and a capacitor connected to the induction coil, a head connected to the wrist and including a housing for receiving the U-shaped pole piece, the two spaced apart ends of the pole piece extending outwardly beyond the housing, and a power source connected to the tank circuit. When the tank circuit is energized and a susceptor is placed in juxtaposition to the ends of the U-shaped pole piece, the susceptor is heated by induction heating due to a magnetic flux passing between the two ends of the pole piece.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Flexible heating head for induction heating (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An induction heating head includes a length of wire having first and second opposite ends and being wound in a flat spiral shape to form an induction coil, a capacitor connected to the first and second ends of the wire, the induction coil and capacitor defining a tank circuit, and a flexible, elastomeric body molded to encase the induction coil. When a susceptor is placed in juxtaposition to the body, and the tank circuit is powered, the susceptor is inductively heated.
    Keywords: COMMUNICATIONS AND RADAR
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Induction heating coupler (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An induction heating device includes a handle having a hollow interior and two opposite ends, a wrist connected to one end of the handle, a U-shaped pole piece having two spaced apart ends, a tank circuit including an induction coil wrapped around the pole piece and a capacitor connected to the induction coil, a head connected to the wrist and including a housing for receiving the U-shaped pole piece, the two spaced apart ends of the pole piece extending outwardely beyond the housing, and a power source connected to the tank circuit. When the tank circuit is energized and a susceptor is placed in juxtaposition to the ends of the U-shaped pole piece, the susceptor is heated by induction heating due to magnetic flux passing between the two ends of the pole piece.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Toroid Joining Gun For Fittings And Couplings (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Hand-held gun used to join metal heat-to-shrink couplings. Uses magnetic induction (eddy currents) to produce heat in metal coupling, and thermocouple to measure temperature and signals end of process. Gun, called "toroid joining gun" concentrates high levels of heat in localized areas. Reconfigured for use on metal heat-to-shrink fitting and coupling applications. Provides rapid heating, operates on low power, lightweight and portable. Safe for use around aircraft fuel and has no detrimental effects on surrounding surfaces or objects. Reliable in any environment and under all weather conditions. Gun logical device for taking full advantage of capabilities of new metal heat-to-shrink couplings and fittings.
    Keywords: FABRICATION TECHNOLOGY
    Type: LAR-14278 , NASA Tech Briefs (ISSN 0145-319X); 16; 12; P. 77
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Integrator Circuitry for Single Channel Radiation Detector (2008)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Input circuitry is provided for a high voltage operated radiation detector to receive pulses from the detector having a rise time in the range of from about one nanosecond to about ten nanoseconds. An integrator circuit, which utilizes current feedback, receives the incoming charge from the radiation detector and creates voltage by integrating across a small capacitor. The integrator utilizes an amplifier which closely follows the voltage across the capacitor to produce an integrator output pulse with a peak value which may be used to determine the energy which produced the pulse. The pulse width of the output is stretched to approximately 50 to 300 nanoseconds for use by subsequent circuits which may then use amplifiers with lower slew rates.
    Keywords: Electronics and Electrical Engineering
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Processing circuitry for single channel radiation detector (2009)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Processing circuitry is provided for a high voltage operated radiation detector. An event detector utilizes a comparator configured to produce an event signal based on a leading edge threshold value. A preferred event detector does not produce another event signal until a trailing edge threshold value is satisfied. The event signal can be utilized for counting the number of particle hits and also for controlling data collection operation for a peak detect circuit and timer. The leading edge threshold value is programmable such that it can be reprogrammed by a remote computer. A digital high voltage control is preferably operable to monitor and adjust high voltage for the detector.
    Keywords: Electronics and Electrical Engineering
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    The NASA/GSFC Advanced Data Grid: A Prototype for Future Earth Science Ground System Architectures (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Contents include the following: Background and motivation. Grid computing concepts. Advanced data grid (ADG) prototype development. ADG requirements and operations concept. ADG architecture. ADG implementation. ADG test plan. ADG schedule. Summary and status.
    Keywords: Computer Programming and Software
    Type: Ground System Architectures Workshop; Mar 04, 2003 - Mar 06, 2003; Manhattan Beach, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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