Aeroelastic Analysis of a Hingeless Rotor Blade in Forward Flight

AIAA Journal ◽  
2000 ◽  
Vol 38 (5) ◽  
pp. 843-850 ◽  
Author(s):  
Seong Min Jeon ◽  
In Lee
Keyword(s):  
Rotor Blade ◽  
Forward Flight ◽  
Aeroelastic Analysis

Aeroelastic analysis of a hingeless rotor blade in forward flight

AIAA Journal ◽  
2000 ◽  
Vol 38 ◽  
pp. 843-850
Author(s):  
Seong M. Jeon ◽  
In Lee
Keyword(s):  
Rotor Blade ◽  
Forward Flight ◽  
Aeroelastic Analysis

Design optimization of helicopter rotor using kriging

2018 ◽  
Vol 90 (6) ◽  
pp. 937-945 ◽  
Author(s):  
Saijal Kizhakke Kodakkattu ◽  
Prabhakaran Nair ◽  
Joy M.L.
Keyword(s):  
Rotor Blade ◽  
Optimization Problem ◽  
Torsional Stiffness ◽  
Helicopter Rotor ◽  
Vibration Level ◽  
Content Type ◽  
Aeroelastic Analysis ◽  
Kriging Metamodel ◽  
Helicopter Rotor Blade ◽  
Trailing Edge Flaps

Purpose The purpose of this study is to obtain optimum locations, peak deflection and chord of the twin trailing-edge flaps and optimum torsional stiffness of the helicopter rotor blade to minimize the vibration in the rotor hub with minimum requirement of flap control power. Design/methodology/approach Kriging metamodel with three-level five variable orthogonal array-based data points is used to decouple the optimization problem and actual aeroelastic analysis. Findings Some very good design solutions are obtained using this model. The best design point in minimizing vibration gives about 81 per cent reduction in the hub vibration with a penalization of increased flap power requirement, at normal cruise speed of rotor-craft flight. Practical implications One of the major challenges in the helicopters is the high vibration level in comparison with fixed wing aircraft. The reduction in vibration level in the helicopter improves passenger and crew comfort and reduces maintenance cost. Originality/value This paper presents design optimization of the helicopter rotor blade combining five design variables, such as the locations of twin trailing-edge flaps, peak deflection and flap chord and torsional stiffness of the rotor. Also, this study uses kriging metamodel to decouple the complex aeroelastic analysis and optimization problem.

Response of Rotor Blades to Random Loads under Forward Flight Conditions

1973 ◽  
Vol 24 (4) ◽  
pp. 252-260 ◽  
Author(s):  
C Lakshmikantham ◽  
K S Aravamudan
Keyword(s):  
Rotor Blade ◽  
Random Excitation ◽  
Rotor Blades ◽  
Linear Dynamical System ◽  
Forward Flight ◽  
Filtering Theory ◽  
Random Loads ◽  
Helicopter Rotor Blade ◽  
System Equations ◽  
Blade Model

SummaryThis paper contains results for the response of a helicopter rotor blade under stationary random excitation when the helicopter is in forward flight. The blade model takes into account the bending and torsional modes as well as the root-rigidity conditions. The resulting linear dynamical system equations with periodic coefficients are treated within the framework of the filtering theory to yield matrix ordinary differential equations for the required response-statistics themselves.

scholarly journals Aeroelastic analysis and structural parametric design of composite rotor blade

2020 ◽  
Author(s):  
Li MA ◽  
Qijun ZHAO ◽  
Kai ZHANG ◽  
Xiayang ZHANG ◽  
Mengmeng ZHAO
Keyword(s):  
Rotor Blade ◽  
Parametric Design ◽  
Aeroelastic Analysis
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