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Kinematic properties of the helicopter in coordinated turnsA study on the kinematic relationship of the variables of helicopter motion in steady, coordinated turns involving inherent sideslip is described. A set of exact kinematic equations which govern a steady coordinated helical turn about an Earth referenced vertical axis is developed. A precise definition for the load factor parameter that best characterizes a coordinated turn is proposed. Formulas are developed which relate the aircraft angular rates and pitch and roll attitudes to the turn parameters, angle of attack, and inherent sideslip. A steep, coordinated helical turn at extreme angles of attack with inherent sideslip is of primary interest. The bank angle of the aircraft can differ markedly from the tilt angle of the normal load factor. The normal load factor can also differ substantially from the accelerometer reading along the vertical body axis of the aircraft. Sideslip has a strong influence on the pitch attitude and roll rate of the helicopter. Pitch rate is independent of angle of attack in a coordinated turn and in the absence of sideslip, angular rates about the stability axes are independent of the aerodynamic characteristics of the aircraft.
Document ID
19810013509
Document Type
Technical Publication (TP)
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
September 4, 2013
Publication Date
April 1, 1981
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
NASA-TP-1773
A-8399
Funding Number(s)
PROJECT: RTOP 505-42-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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