Add to ORKGIn the present investigation, the helicopter blade is modeled as a rotating beam with two degrees of freedom, namely the elastic flatwise bending and torsion. A mathematical model in the frequency domain is developed, incorporating the unsteady aerodynamic loads associated with helicopters in forward flight. The effects of dynamic adaptation of the rot boundary conditions on the beam aeroelastic response are studied. The results suggest that it is possible to control the local dynamic response at particular sections of the beam by varying the frequency and relative phase of the control signal
An individual blade controller designed to attenuate the aeroelastic response of helicopter rotors i...
Active vibration control is a widely implemented method for the helicopter vibration control. Due to...
The feasibility studies of a new solution for the individual blade control aiming at helicopter vibr...
In the present investigation, the helicopter blade is modelled as a rotating beam with two degrees o...
This paper investigates the feasibility of employing adaptive material to build both sensors and act...
A flight dynamics model based on elastic blades for helicopters is developed. Modal shape analysis i...
Abstract. This paper describes the fundamental design approach of a mechanical device using smart st...
In the present paper, the aeroelastic stability of helicopter rotor blade is determined using Aeroel...
Applying adaptronics to helicopters has a high potential to significantly suppress noise, reduce vib...
Applying adaptronics to helicopters has a high potential to significantly suppress noise, reduce vib...
Governing equations are obtained for helicopter rotor blades with surface bonded piezoceramic actuat...
In this paper, the time-dependent non-linear partial differential equations of motion for both canti...
Applying adaptronics to helicopters has a high potential to significantly suppress noise, reduce vib...
A set of nonlinear, intrinsic equations describing the dynamics of beam structures under-going large...
International audienceThe dynamic loads transmitted from the rotor to the airframe are responsible f...
An individual blade controller designed to attenuate the aeroelastic response of helicopter rotors i...
Active vibration control is a widely implemented method for the helicopter vibration control. Due to...
The feasibility studies of a new solution for the individual blade control aiming at helicopter vibr...
In the present investigation, the helicopter blade is modelled as a rotating beam with two degrees o...
This paper investigates the feasibility of employing adaptive material to build both sensors and act...
A flight dynamics model based on elastic blades for helicopters is developed. Modal shape analysis i...
Abstract. This paper describes the fundamental design approach of a mechanical device using smart st...
In the present paper, the aeroelastic stability of helicopter rotor blade is determined using Aeroel...
Applying adaptronics to helicopters has a high potential to significantly suppress noise, reduce vib...
Applying adaptronics to helicopters has a high potential to significantly suppress noise, reduce vib...
Governing equations are obtained for helicopter rotor blades with surface bonded piezoceramic actuat...
In this paper, the time-dependent non-linear partial differential equations of motion for both canti...
Applying adaptronics to helicopters has a high potential to significantly suppress noise, reduce vib...
A set of nonlinear, intrinsic equations describing the dynamics of beam structures under-going large...
International audienceThe dynamic loads transmitted from the rotor to the airframe are responsible f...
An individual blade controller designed to attenuate the aeroelastic response of helicopter rotors i...
Active vibration control is a widely implemented method for the helicopter vibration control. Due to...
The feasibility studies of a new solution for the individual blade control aiming at helicopter vibr...