A PILOTED SIMULATOR INVESTIGATION OF STATIC STABILITY AND STABILITY CONTROL AUGMENTATION EFFECTS ON HELICOPTER HANDLING QUALITIES FOR INSTRUMENT APPROACH

A motion-base simulator was used to compare the flying qualities of three generic single-rotor helicopters during a full-attention-to-flight control task. Terminal-area VOR instrument approaches were flown with and without turbulence. The objective of this NASA/FAA study was to investigate the influence of helicopter static stability in terms of the values of cockpit control gradients as specified in the existing airworthiness criteria, and to examine the effectiveness of several types of stability control augmentation systems in improving the instrument-flight-rules capability of helicopters with reduced static stability. Two levels of static stability in the pitch, roll, and yaw axes were examined for a hingeless-rotor configuration; the variations were stable and neutral static stability in pitch and roll, and two levels of stability in yaw. For the lower level of static stability, four types of stability and control augmentation were also examined for helicopters with three rotor types: hingeless, articulated, and teetering. Pilot rating results indicate the acceptability of neutral static stability longitudinally and laterally and the need for pitch-roll attitude augmentation to achieve a satisfactory system. (Author)

  • Corporate Authors:

    National Aeronautics and Space Administration

    Ames Research Center
    Moffett Field, CA  USA  94035

    Federal Aviation Administration

    800 Independence Avenue, SW
    Washington, DC  USA  20591
  • Authors:
    • Lebacqz, J V
    • Forrest, R D
    • Gerdes, R M
  • Publication Date: 1980-9

Media Info

  • Pagination: 393 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00328918
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-A-8125, NASA-TM-81188
  • Files: NTIS, USDOT
  • Created Date: May 21 2002 12:00AM