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  • 1
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    Identification of a coupled flapping/inflow model for the PUMA helicopter from flight test data (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A model validation procedure is applied to a coupled flapping/inflow model of a PUMA helicopter blade. The structure of the baseline model is first established. Model structure and flight test data are checked for consistency. Parameters of the model are then identified from the flight test data.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Vertica (ISSN 0360-5450); 13; 3, 19; 267-280
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A real-time blade element helicopter simulation for handling qualities analysis (1989)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: A simulation model which utilizes parallel processing platforms is described in terms of its contributions to improved real-time helicopter simulation. The FLIGHTLAB parallel processing environment is explained, and the relative advantages of the blade element and rotor map models for rigid and elastic articulated blades are discussed. A UH-60 simulation is conducted by means of a rigid model with 14 degrees of freedom, as well as an elastic model with 26 degrees of freedom, to compare trim conditions, longitudinal static margins, and longitudinal and lateral frequency responses. The FLIGHTLAB system is shown to facilitate restructuring for parallel processing as well as the systematic comparison of a variety of models. The system can facilitate the comparison of rigid and elastic blade element rotor models at NASA-Ames and other research facilities.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Design and evaluation of a state-feedback vibration controller (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The effectiveness and practicality of the state-feedback vibration controller is demonstrated by computer simulations. It is shown that: (1) the required measurements can be reduced to fuselage accelerations; (2) the system is stable over a wide range of flight conditions; (3) a discrete design for the controller provides effective digital implementation at 80-Hz sampling; (4) attenuation produced by the actuators does not create a problem, and a simple lead compensator provides vibration reduction; and (5) a design based on a hover model worked well at five knots. At 40 and 120 knots, vibrations in all but the vertical acceleration were effectively suppressed. The state-feedback vibration controller has a rapid convergence time and implementation is easier than with multicyclic control since no on-line harmonic analysis or identification algorithms are required.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AHS PREPRINT 81-10 , Northeast Region National Specialists'' Meeting on Helicopter Vibration: Technology for the Jet Smooth Ride; Nov 02, 1981 - Nov 04, 1981; Hartford, CT
    Format: text
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    NASA TECHNICAL REPORTS
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