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  • Articles
  • Other Sources  (43)
  • NASA Technical Reports  (43)
  • Bibliography on Seismology
  • AIRCRAFT STABILITY AND CONTROL  (43)
  • 1980-1984  (43)
  • 1965-1969
  • 1983  (43)
  • 1
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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
  • 2
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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
  • 3
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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
  • 4
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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
  • 5
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    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
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  • 6
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    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
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    NASA TECHNICAL REPORTS
  • 7
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    Self-repairing Digital Flight Control System (1983)
    In:  CASI
    Details
    Publication Date: 2014-09-11
    Description: Self-repairing digital flight control systems and aircraft battle damage repair are addressed.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA. Langley Research Center Restructurable Controls; p 133-160
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  • 8
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    Trimming advanced fighters for STOL approaches (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 05, p. 598, Accession no. A83-16566
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Aircraft (ISSN 0021-8669); 20; 957-962
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    NASA TECHNICAL REPORTS
  • 9
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    Space Shuttle stability and control derivatives estimated from the first entry (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 03, p. 333, Accession no. A82-13880
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: (ISSN 0731-5090)
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    NASA TECHNICAL REPORTS
  • 10
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    Control of the forebody vortex orientation by asymmetric air injection. Part A: Application to enhance departure/spin recovery of fighter aircraft and Part B: Details of the flow structure (1983)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A concept developed to provide powerful directional control effectiveness for a fighter aircraft at high angles of attack is described. The concept utilizes the energy concentrated in the strong forebody vortices (which form on slender bodies of high relative incidence) by controlling the lateral orientation of the vortices with respect to the body. The objective was to utilize the side force associated with asymmetric vortices, in a controlled manner, to enhance the ability of the fighter to recover from a departure from controlled flight. The results from water tunnel and wind tunnel experiments show that a small amount of tangential blowing along the forebody near the apex can effectively alter the forebody vortex system and generate large restoring yawing moments. Six degree of freedom digital simulation results show that this concept can substantially enhance recovery characteristics of fighter aircraft with long, slender forebodies. Also, the results of experiments which were conducted on a cone model are discussed where the principal test objective was to develop an understanding of the fluid mechanics involved in the process of vortex control. Knowledge gained in these more generic tests should allow the concept to be applied to a wider range of configurations.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AGARD Spec. Course on Aerodyn. Characteristics of Controls; 22 p
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    NASA TECHNICAL REPORTS
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