ALBERT

All Library Books, journals and Electronic Records Telegrafenberg

X
feed icon rss

Your email was sent successfully. Check your inbox.

An error occurred while sending the email. Please try again.

Proceed reservation?

Export
Filter
  • Articles
  • Other Sources  (82)
  • NASA Technical Reports  (82)
  • Bibliography on Seismology
  • AIRCRAFT STABILITY AND CONTROL  (43)
  • AIRCRAFT PROPULSION AND POWER  (39)
  • 1980-1984  (82)
  • 1965-1969
  • 1983  (82)
Collection
  • Articles
  • Other Sources  (82)
Source
  • NASA Technical Reports  (82)
  • Bibliography on Seismology
Keywords
Years
  • 1980-1984  (82)
  • 1965-1969
Year
  • 1
    facet.materialart.
    Unknown
    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
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Ejector nozzle test results at simulated flight conditions for an advanced supersonic transport propulsion system (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results are presented of wind tunnel tests conducted to verify the performance improvements of a refined ejector nozzle design for advanced supersonic transport propulsion systems. The analysis of results obtained at simulated engine operating conditions is emphasized. Tests were conducted with models of approximately 1/10th scale which were configured to simulate nozzle operation at takeoff, subsonic cruise, transonic cruise, and supersonic cruise. Transonic cruise operation was not a consideration during the nozzle design phase, although an evaluation at this condition was later conducted. Test results, characterized by thrust and flow coefficients, are given for a range of nozzle pressure ratios, emphasizing the thrust performance at the engine operating conditions predicted for each flight Mach number. The results indicate that nozzle performance goals were met or closely approximated at takeoff and supersonic cruise, while subsonic cruise performance was within 2.3 percent of the goal with further improvement possible.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 83-1287
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 3
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 5
    facet.materialart.
    Unknown
    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
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 6
    facet.materialart.
    Unknown
    A Preliminary Study of Solar Powered Aircraft and Associated Power Trains (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The feasibility of regeneratively powered solar high altitude powered platform (HAPP) remotely piloted vehicles was assessed. Those technologies which must be pursued to make long duration solar HAPPs feasible are recommended. A methodology which involved characterization and parametric analysis of roughly two dozen variables to determine vehicles capable of fulfilling the primary mission are defined. One of these vehicles was then conceptually designed. Variations of each major design parameter were investigated along with state-of-the-art changes in power train component capabilities. The midlatitude mission studied would be attainable by a solar HAPP if fuel cell, electrolyzer and photovoltaic technologies are pursued. Vehicles will be very large and have very lightweight structures in order to attain the combinations of altitude and duration required by the primary mission.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-3699 , NAS 1.26:3699
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Qualification of the flight-critical AFTI/F-16 digital flight control system (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Qualification considerations for assuring the safety of a life-critical digital flight control system include four major areas: systems interactions, verification, validation, and configuration control. The AFTI/F-16 design, development, and qualification illustrate these considerations. In this paper, qualification concepts, procedures, and methodologies are discussed and illustrated through specific examples.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 83-0060 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 8
    facet.materialart.
    Unknown
    A variable-geometry combustor used to study primary and secondary zone stoichiometry (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A combustion program is underway to evaluate fuel quality effects on gas turbine combustors. A rich-lean variable geometry combustor design was chosen to evaluate fuel quality effects over a wide range of primary and secondary zone equivalence ratios at simulated engine operating conditions. The first task of this effort, was to evaluate the performance of the variable geometry combustor. The combustor incorporates three stations of variable geometry to control primary and secondary zone equivalence ratio and overall pressure loss. Geometry changes could be made while a test was in progress through the use of remote control actuators. The primary zone liner was water cooled to eliminate the concern of liner durability. Emissions and performance data were obtained at simulated engine conditions of 80 percent and full power. Inlet air temperature varied from 611 to 665K, inlet total pressure varied from 1.02 to 1.24 MPa, reference velocity was a constant 1400 K.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-83372 , E-1640 , NAS 1.15:83372 , Joint Power Generation Conf.; Sep 25, 1983 - Sep 29, 1983; Indianapolis
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 9
    facet.materialart.
    Unknown
    AFTI/F-16 flight test results and lessons (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The advanced fighter technology integration (AFTI) F-16 aircraft is a highly complex digital flight control system integrated with advanced avionics and cockpit. The use of dissimilar backup modes if the primary system fails requires the designer to trade off system simplicity and capability. The tradeoff is evident in the AFTI/F-16 aircraft with its limited stability and fly by wire digital flight control systems when a generic software failure occurs the backup or normal mode must provide equivalent envelop protection during the transition to degraded flight control. The complexity of systems like the AFTI/F-16 system defines a second design issue, which is divided into two segments: (1) the effect on testing, (2) and the pilot's ability to act correctly in the limited time available for cockpit decisions. The large matrix of states possible with the AFTI/F-16 flight control system illustrates the difficulty of both testing the system and choosing real time pilot actions. The third generic issue is the possible reductions in the user's reliability expectations where false single channel information can be displayed at the pilot vehicle interface while the redundant set remains functional.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-84920 , NAS 1.15:84920 , H1206 , Symp. of the Soc. of Exptl. Test Pilots; Sep 28, 1983 - Oct 01, 1983; Beverly Hills, CA; United States
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
  • 10
    facet.materialart.
    Unknown
    Combustion hot section technology (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The overall objective of the Turbine Engine Hot Section Technology Combustion Project is to develop and verify improved and more accurate analysis methods for increasing the ability to design with confidence the combustion system for advanced aircraft turbine engines. The analysis methods developed will be generically applicable to combustion systems and not restricted to one specific engine or manufacturer. This project's approach was to first assess and evaluate existing combustor aerothermal analysis models by means of a contracted effort initiated during FY 1982. This evaluation effort has assessed and quantified known models' strengths and deficiencies. During FY 1984 the Aerothermal Modeling Program, Phase 2 will be initiated, which is expected to have contracted model development efforts in the areas of improved numerical methods for turbulent viscous flows, flow interactions, and fuel spray flow foekd interactions. A Phase 3 effort is planned to address remaining model deficiencies. The primary inhouse effort in this area will be the determination of high pressure flame radiation characteristics in a full annular combustor. This experiment will be conducted in the NASA LeRC High Pressure Facility with the results compiled into a comprehensive flame radiation and liner heat flux model.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Turbine Eng. Hot Sect. Technol. (HOST); p 129-133
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
Close ⊗
This website uses cookies and the analysis tool Matomo. More information can be found here...