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  • Articles
  • Other Sources  (85)
  • NASA Technical Reports  (85)
  • Bibliography on Seismology
  • AIRCRAFT STABILITY AND CONTROL  (43)
  • ELECTRONICS AND ELECTRICAL ENGINEERING  (42)
  • 1980-1984  (85)
  • 1965-1969
  • 1983  (85)
Collection
  • Articles
  • Other Sources  (85)
Source
  • NASA Technical Reports  (85)
  • Bibliography on Seismology
Keywords
Years
  • 1980-1984  (85)
  • 1965-1969
Year
  • 1
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    Modeling a Li/SOCl2 battery for design purposes (1983)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: A generalized code applicable to many different electrochemical systems and geometric designs is discussed. The code is to be set up so that physical property data such as thermal conductivity, viscosity, density, and configuration (e.g. physical dimensions) are the input data. Thus, by changing these parameters many different battery configurations can be handled. The outputs, as a function of time and space, are voltage, current, temperature, pressure, velocity, and species concentration.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: NASA. Goddard Space Flight Center The 1982 Goddard Space Flight Center Battery Workshop; p 178-199
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    AFTI/F-16 DFCS development summary - A report to industry multimode control law design (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The primary goal of the AFTI/F-16 program is to develop a reliable triplex digital multimode flight control system; this system is to be tailored to optimize fighter performance and capable of six-degree-of-freedom decoupled aircraft control. The multiple digital control law configurations arrived at through flight testing are presented. The changes in these designs from the results of flight tests establish that flight testing is an integral part of the development process. The flight test results are analyzed here from the standpoint of pilot comments and resulting control law design modifications.
    Keywords: AIRCRAFT STABILITY AND CONTROL
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    NASA TECHNICAL REPORTS
  • 3
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    High-current, high-frequency capacitors (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The NASA Lewis high-current, high-frequency capacitor development program was conducted under a contract with Maxwell Laboratories, Inc., San Diego, California. The program was started to develop power components for space power systems. One of the components lacking was a high-power, high-frequency capacitor. Some of the technology developed in this program may be directly usable in an all-electric airplane. The materials used in the capacitor included the following: the film is polypropylene, the impregnant is monoisopropyl biphenyl, the conductive epoxy is Emerson and Cuming Stycast 2850 KT, the foil is aluminum, the case is stainless steel (304), and the electrode is a modified copper-ceramic.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Aircraft Elect. Secondary Power; p 149-158
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A helicopter flight investigation of roll-control sensitivity, damping and cross coupling in a low altitude lateral maneuvering task (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A helicopter in-flight simulation was conducted to determine the effects of variations in roll damping, roll sensitivity, and pitch and roll rate cross-coupling on helicopter flying qualities in a low altitude maneuver. The experiment utilized the UH-1H helicopter in-flight simulator, which is equipped with the V/STOLAND avionics system. The response envelope of this vehicle allowed simulation of configurations with low to moderate damping and sensitivity. A visual, low level slalom course was set up, consisting of constant speed and constant altitude S-turns around the 1000 ft makers of an 8000 ft runway. Results are shown in terms of Cooper-Harper pilot ratings, pilot commentary, and statistical and frequency analyses of the lateral characteristics. These results show good consistency with previous ground simulator results and are compared with existing flying qualities criteria.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-84376 , A-9431 , NAS 1.15:84376
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Additive for zinc electrodes (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A zinc electrode for alkaline cells includes up to about ten percent by weight of Ba(OH)2.8H2O with about five percent being preferred. The zinc electrode may or may not be amalgamated with mercury.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Space Shuttle flying qualities and flight control system assessment study, phase 2 (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A program of flying qualities experiments as part of the Orbiter Experiments Program (OEX) is defined. Phase 1, published as CR-170391, reviewed flying qualities criteria and shuttle data. The review of applicable experimental and shuttle data to further define the OEX plan is continued. An unconventional feature of this approach is the use of pilot strategy model identification to relate flight and simulator results. Instrumentation, software, and data analysis techniques for pilot model measurements are examined. The relationship between shuttle characteristics and superaugmented aircraft is established. STS flights 1 through 4 are reviewed from the point of view of flying qualities. A preliminary plan for a coordinated program of inflight and simulator research is presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-170406 , NAS 1.26:170406 , REPT-1187-1R
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flight-test of the glide-slope track and flare-control laws for an automatic landing system for a powered-lift STOL airplane (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An automatic landing system was developed for the Augmentor Wing Jet STOL Research Airplane to establish the feasibility and examine the operating characteristics of a powered-lift STOL transport flying a steep, microwave landing system (MLS) glide slope to automatically land on a STOL port. The flight test results address the longitudinal aspects of automatic powered lift STOL airplane operation including glide slope tracking on the backside of the power curve, flare, and touchdown. Three different autoland control laws were evaluated to demonstrate the tradeoff between control complexity and the resulting performance. The flight test and simulation methodology used in developing conventional jet transport systems was applied to the powered-lift STOL airplane. The results obtained suggest that an automatic landing system for a powered-lift STOL airplane operating into an MLS-equipped STOL port is feasible. However, the airplane must be provided with a means of rapidly regulation lift to satisfactorily provide the glide slope tracking and control of touchdown sink rate needed for automatic landings.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2128 , A-9199 , NAS 1.60:2128
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A 20-GHz IMPATT diode development (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The development of 20 GHz, double drift GaAs IMPATT diodes is described. Advances made in material growth, diodes fabrication technology and packaging, and circuit design and diode testing are documented.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: S-3057 , TRW Electronic Systems Group A 20-GHz IMPATT Transmitter; 103 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Image-optimized, frequency-scalable mixers for millimeter-wave applications (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A unique IF measurement procedure for evaluating mixer performance and identifying optimum circuit boundary conditions is presented. The technique is applied to a scalable mm-wave single-sideband (image-sum enhanced) mixer design which provides 3.5 to 5 dB typical conversion loss from conventional, packaged devices.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
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    NASA TECHNICAL REPORTS
  • 10
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    GaInAs-AlInAs heterostructures for optical devices grown by MBE (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The band gap of Ga(0.47)In(0.53)As corresponds to an emission wavelength of about 1.65 microns. Lasers have been produced with Al(0.48)In(0.52)As as cladding layers operating at room temperature. The peak emission of Ga(0.47)In(0.53)As can be continuously varied from 1.65 to 1.2 microns by the use of the multiquantum well structures. This range of wavelengths covers the minimum loss and dispersion in optical fibers and will be applicable to integrated optics. Double heterostructure broad area lasers have been fabricated using AlInAs as cladding layers to the GaInAs active layer. Room temperature threshold current densities of 4.3 kA/sq cm have been obtained for lasers with a 4500 A active region. The first data on GaInAs/AlInAs quantum well emitters will be presented. Photoluminescence of 4 K from quantum well layers of 100, 150, and 180 A with 150 A AlInAs barrier layers produced emission at 1.27, 1.35, and 1.41 microns, respectively. Ga(0.47)In(0.52)As quantum well LEDs have also been produced which emit at 1.34 microns.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Journal of Vacuum Science and Technology B (ISSN 0734-211X); 1; 202-204
    Format: text
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    NASA TECHNICAL REPORTS
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