NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
An active control system for helicopter vibration reduction by higher harmonic pitchAn analytical study defining the basic configuration of an active control system to reduce helicopter vibrations is presented. Theoretical results for a nonlinear four-bladed single rotor helicopter simulation are discussed, showing that vibration reductions on the order of 80-90% for airspeeds up to 150 kn can be expected when using a higher harmonic pitch in an active feedback control system. The rotor performance penalty associated with this level of vibration reduction is about 1-3% and the increase in rotor blade stresses is considered to be low. The location of sensor accelerometers proved to be significant for vibration reductions, and it is noted that the RTSA controller is tolerant of sensor signal noise.
Document ID
19810055785
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Taylor, R. B.
(United Technologies Research Center East Hartford, CT, United States)
Farrar, F. A.
(United Technologies Research Center East Hartford, CT, United States)
Miao, W.
(United Technologies Corp. Sikorsky Aircraft Div., Stratford, CT, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1980
Subject Category
Aircraft Stability And Control
Report/Patent Number
AHS 80-71
Meeting Information
Meeting: Annual Forum of the American Helicopter Society
Location: Washington, DC
Start Date: May 13, 1980
End Date: May 15, 1980
Sponsors: American Helicopter Society
Accession Number
81A40189
Funding Number(s)
CONTRACT_GRANT: NAS2-101211
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available