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  • 1
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    Flexible aircraft flying and ride qualities (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A brief analytic exposition is presented to illustrate a central principle in flexible mode control, some of the pertinent pilot centered requirements are listed and discussed. The desired features of the control methodology are exposed and the methodology to be used is selected. The example Boeing supplied characteristics are discussed and approximated with a reduced order model and a simplified treatment of unsteady aerodynamics. The closed loop flight control system design follows, along with first level assessments of resulting handling and ride quality characteristics. Some of these do not meet the postulated requirements and remain problems to be solved possibly by further analysis or future simulation.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA. Langley Research Center NASA Aircraft Controls Research, 1983; p 69-92
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The Development of a Lateral-control System for Use with Large-span Flaps (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A spoiler-type lateral-control system has been developed for use on the Northrop P-61 airplane. The lateral-control system is to be used with large-span flaps and consists of a thin circular arc spoiler, linked with a short-span plain aileron located just outboard of the spoiler. This unconventional lateral-control system has been accepted with enthusiasm by the pilots who have flown the airplane. The particularly appreciate its characteristic at high speed. The combination of light forges, favorable yawing moment, and low wing torsional moments, make it a very effective, easily applied control. The control available at and through the stall is also remarkably good, although this characteristic may be attributed, in part, to an exceptionally good wing stalling pattern rather than entirely to the use of the spoiler-type aileron. In the landing configuration, the lateral-control effectiveness increases automatically with the extension of wing flaps so that powerful control is available during the approach. There is, however, a decrease in effectiveness for the first 5 percent of the wheel travel with a resultant tendency for inexperienced pilots to overcontrol slightly at low speeds. The fact that the aileron can be fully used at the stall, however, more than compensates for this loss of effectiveness with flaps down and greatly enhances the airplane's landing performance.
    Type: NACA-TN-1015
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Mission-oriented requirements for updating MIL-H-8501. Volume 1: STI proposed structure (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The structure of a new flying and ground handling qualities specification for military rotorcraft is presented. This preliminary specification structure is intended to evolve into a replacement for specification MIL-H-8501A. The new structure is designed to accommodate a variety of rotorcraft types, mission flight phases, flight envelopes, and flight environmental characteristics and to provide criteria for three levels of flying qualities, a systematic treatment of failures and reliability, both conventional and multiaxis controllers, and external vision aids which may also incorporate synthetic display content. Existing and new criteria were incorporated into the new structure wherever they could be substantiated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-177331-VOL-1 , NAS 1.26:177331-VOL-1 , USAAVSCOM-TR-84-A-6-VOL-1 , STI-TR-1194-1-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Analyses of shuttle orbiter approach and landing conditions (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A study of one shuttle orbiter approach and landing conditions are summarized. Causes of observed PIO like flight deficiencies are identified and potential cures are examined. Closed loop pilot/vehicle analyses are described and path/attitude stability boundaries defined. The latter novel technique proved of great value in delineating and illustrating the basic causes of this multiloop pilot control problem. The analytical results are shown to be consistent with flight test and fixed base simulation. Conclusions are drawn relating to possible improvements of the shuttle orbiter/digital flight control system.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-163108 , TR-1137-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Analyses of Shuttle Orbiter approach and landing (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Previously cited in issue 19, p. 2989, Accession no. A82-39014
    Keywords: SPACE TRANSPORTATION
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 6; 448-455
    Format: text
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  • 6
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    Flight dynamics analysis and simulation of heavy lift airships. Volume 5: Programmer's manual (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Programmer's Manual contains explanations of the logic embodied in the various program modules, a dictionary of program variables, a subroutine listing, subroutine/common block/cross reference listing, and a calling/called subroutine cross reference listing.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-166471-VOL-5 , NAS 1.26:166471-VOL-5 , TR-1151-2-VOL-5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flight dynamics analysis and simulation of heavy lift airships. Volume 1: Executive summary (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A generic, yet comprehensive mathematical model and computer simulation of the HLA flight dynamics over its entire flight envelope was developed. Implicit in this simulation development are the data reviews and analyses which support the equations of motion and the calculation of forces and moments acting on the vehicle. The simulation, HYBRDS, is addressed to the broad requirements and is intended for use as a synthesis and analysis tool for the evaluation of competing HLA design concepts.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-166471-VOL-1 , NAS 1.26:166471-VOL-1 , TR-1151-2-VOL-1
    Format: application/pdf
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  • 8
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    Flight dynamics analysis and simulation of heavy lift airships. Volume 2: Technical manual (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The mathematical models embodied in the simulation are described in considerable detail and with supporting evidence for the model forms chosen. In addition the trimming and linearization algorithms used in the simulation are described. Appendices to the manual identify reference material for estimating the needed coefficients for the input data and provide example simulation results.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-166471-VOL-2 , NAS 1.26:166471-VOL-2 , TR-1151-2-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Analysis and moving base simulation of transition configuration management aspects of a powered lift aircraft (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study aimed at the implementation of a configuration management flight control system is reported. The system is designed to take the guesswork out of, and improve the operational safety of, transition flight in the region from cruise to STOL. Potential improvements in the trim configuration management aspects of the transition process are described.
    Keywords: AIRCRAFT
    Type: NASA-CR-114698 , STI-TR-1015-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Helistat simulation studies (1982)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An analysis of the flight dynamics and piloted control characteristics of the Helistat, a quadrotor heavy-lift airship, was completed using the HYBRDS airship simulation facility. The analysis covered the full operating flight envelope, including likely ranges of altitude, airspeed, sideslip, and loading variations. Particular areas of study were performance, trim, power requirements, linearized dynamics, handling qualities, and mooring operations. The key assumptions were: a rigid vehicle, no control system dynamics, fixed rotor and propeller RPM, and no ballonet dynamics. The nominal cruise speed for the H34 engines operating at 1275 HP was found to be 40-50 kts, depending on the loading condition. The maximum payload capability was calculated as 45,000 lbs for sea level-based operations. The crosswind capability in hover is 5-10 kts depending on the loading conditions, but this requires excessive roll angle due to the roll-to-translate control gearing. Sideslip angles of 110-135 degrees (wind from aft quarters) are critical for directional trim and stability, and should be avoided.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-166567 , NAS 1.26:166567 , STI-TR-1151-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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