Structural Design of an Active Trailing-Edge Flap Blade for Helicopter Vibration Control

2012 ◽  
Author(s):  
Balakumaran Natarajan ◽  
WonJong Eun ◽  
Jaehwan Lee ◽  
Sang Joon Shin
Keyword(s):  
Vibration Control ◽  
Structural Design ◽  
Trailing Edge ◽  
Trailing Edge Flap ◽  
Helicopter Vibration

scholarly journals Structural Design and Analysis upon Active Rotor Blade with Trailing-edge Flap

2012 ◽  
Vol 40 (6) ◽  
pp. 499-505
Author(s):  
Won-Jong Eun ◽  
Balakumaran Natarajan ◽  
Jae-Hwan Lee ◽  
Sang-Joon Shin
Keyword(s):  
Structural Design ◽  
Rotor Blade ◽  
Trailing Edge ◽  
Trailing Edge Flap

scholarly journals Vibration control of cantilever blade based on trailing-edge flap by restricted control input

2021 ◽  
pp. 002029402098337
Author(s):  
Ting-Rui Liu ◽  
Ai-Ling Gong
Keyword(s):  
Vibration Control ◽  
Hardware Implementation ◽  
Control Algorithms ◽  
Linear Matrix ◽  
Control Input ◽  
Trailing Edge ◽  
Flutter Suppression ◽  
Input Signals ◽  
Trailing Edge Flap ◽  
And Control

Vibration and control of cantilever blade with bending-twist coupling (BTC) based on trailing-edge flap (TEF) by restricted control input are investigated. The blade is a thin-walled structure using circumferentially asymmetric stiffness (CAS) configuration, with TEF embedded and hinged into the host composite structure along the entire blade span. The TEF structure is driven by quasi-steady aerodynamic forces. Vibration control is investigated based on linear matrix inequation (LMI) algorithm using restricted control input (LMI/RCI). Flutter suppression of BTC displacements and the angle of TEF (i.e. the practical control input) are illustrated, with apparently controlled effects demonstrated. The restricted control input signals are used to driven the TEF to explore the scope of the feasibility of the practical TEF angle, which is displayed by a virtual simulation platform. The platform verifies the feasibility of the hardware implementation for the control algorithms.

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