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Effects of blade configuration parameters on helicopter rotor structural dynamics and whirl tower loads

Published online by Cambridge University Press:  29 February 2016

M. Rohin Kumar  and
C. Venkatesan
M. Rohin Kumar*
Affiliation:
Department of Aerospace Engineering, Indian Institute of Technology, KanpurIndia
C. Venkatesan
Affiliation:
Department of Aerospace Engineering, Indian Institute of Technology, KanpurIndia
*
[email protected]
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Abstract

The influence of the blade geometric parameters on the structural dynamic characteristics, response and loads of a helicopter rotor under hover condition in a whirl tower was investigated. A general geometry was considered for the rotor blade which included configuration parameters like root offset, torque offset, pre-twist, pre-cone, pre-droop, pre-sweep, tip-sweep and tip-anhedral. The option of placing concentrated masses at any location on the blade was also included. Natural frequencies and the corresponding mode shapes of the rotating blade were obtained by solving the linear, undamped structural dynamics model in the finite element domain. For calculating the response and loads on the rotor, the complete aeroelastic equation was solved in modal space. Aerodynamic models used in the aeroelastic loads calculations were Peters-He dynamic wake theory for inflow and the modified ONERA dynamic stall theory for airloads calculations. From the study, the blade structural dynamic characteristics are found to be sensitive to variation in blade geometric parameters. Tip-sweep was found to have significant effects on root oscillatory moments. The moments at the tip junction with the straight portion of the blade were found to be substantially affected by tip-sweep and tip-anhedral.

Keywords

Structural DynamicsRotor LoadsRotary-wing Aeroelasticity
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1224 , February 2016 , pp. 271 - 290
Copyright
Copyright © Royal Aeronautical Society 2016 

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