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Influence of sideslip on the kinematics of the helicopter in steady coordinated turnsA steep coordinated helical turn at extreme angles of attack with inherent sideslip is of primary interest in this study. Unlike fixed-wing aircraft, the helicopter in a steady coordinated turn will inherently sideslip. A set of exact kinematic equations describing this motion in steady helical turns has been developed, and a rational definition for the load factor that best characterizes a coordinated turn for a helicopter has been proposed. An analysis has also been completed on the effects of sideslip on the kinematic relationships in a coordinated turn which is based on new closed-form solutions which relate the aircraft angular rates and pitch and roll attitudes to the turn parameters, angle of attack, and sideslip. The results show that the bank angle of the aircraft can differ markedly from the tilt angle of the normal load factor and that the normal load factor can also differ substantially from the accelerometer reading along the vertical body axis of the aircraft. Generally, sideslip has a strong influence on the pitch attitude and roll rate of the helicopter. The study also indicates that pitch rate is independent of angle of attack in a coordinated turn and that in the absence of sideslip, angular rates about the stability axes are independent of the aerodynamic characteristics of the aircraft.
Document ID
19810062240
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Chen, R. T. N.
(NASA Ames Research Center Moffett Field, CA, United States)
Jeske, J. A.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Stability And Control
Meeting Information
Meeting: Annual Forum
Location: New Orleans, LA
Start Date: May 17, 1981
End Date: May 20, 1981
Sponsors: American Helicopter Society
Accession Number
81A46644
Distribution Limits
Public
Copyright
Other

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