Application of the finite-state arbitrary-motion aerodynamics to rotor blade aeroelastic response and stability in hover and forward flight

1985 ◽  
Author(s):  
M. DINYAVARI ◽  
P. FRIEDMANN
Keyword(s):  
Rotor Blade ◽  
Forward Flight ◽  
Aeroelastic Response ◽  
Finite State

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

Finite‐State Induced‐Flow Model for Rotors in Hover and Forward Flight

1989 ◽  
Vol 34 (4) ◽  
pp. 5-17 ◽  
Author(s):  
David A. Peters ◽  
David Doug Boyd ◽  
Cheng Jian He
Keyword(s):  
Flow Model ◽  
Forward Flight ◽  
Finite State ◽  
Induced Flow

Helicopter Rotor Blade Flexibility Simulation for Aeroelasticity and Flight Dynamics Applications

2014 ◽  
Vol 59 (4) ◽  
pp. 1-18 ◽  
Author(s):  
Ioannis Goulos ◽  
Vassilios Pachidis ◽  
Pericles Pilidis
Keyword(s):  
Real Time ◽  
Rotor Blade ◽  
Flight Dynamics ◽  
Integrated Approach ◽  
Flight Simulation ◽  
Response Characteristics ◽  
Helicopter Flight ◽  
Finite State ◽  
The Time Domain ◽  
Blade Loads

This paper presents a mathematical model for the simulation of rotor blade flexibility in real-time helicopter flight dynamics applications that also employs sufficient modeling fidelity for prediction of structural blade loads. A matrix/vector-based formulation is developed for the treatment of elastic blade kinematics in the time domain. A novel, second-order-accurate, finite-difference scheme is employed for the approximation of the blade motion derivatives. The proposed method is coupled with a finite-state induced-flow model, a dynamic wake distortion model, and an unsteady blade element aerodynamics model. The integrated approach is deployed to investigate trim controls, stability and control derivatives, nonlinear control response characteristics, and structural blade loads for a hingeless rotor helicopter. It is shown that the developed methodology exhibits modeling accuracy comparable to that of non-real-time comprehensive rotorcraft codes. The proposed method is suitable for real-time flight simulation, with sufficient fidelity for simultaneous prediction of oscillatory blade loads.

Aeroelastic response of a propulsive rotor blade with synthetic jets

2021 ◽  
Vol 107 ◽  
pp. 103411
Author(s):  
Victor Maldonado ◽  
Nicolas Peralta ◽  
Serdar Gorumlu ◽  
Wolduamlak Ayele ◽  
Dioser Santos
Keyword(s):  
Rotor Blade ◽  
Synthetic Jets ◽  
Aeroelastic Response

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.

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