منابع مشابه
Electrochemically-actuated Morphing Helicopter Blade
The use of the expansion of lithium-ion cells for mechanical actuation has been recently reported by Chin et. al. (1). Under a stress of 10 MPa, actuating strains of up to 1.5% were achieved. Taking into account the cells approximate elastic modulus, this strain corresponds to a mechanical energy density ten times higher than that of current piezoelectric materials, although with slower actuati...
متن کاملAnalysis of Stresses in Helicopter Composite blade in Hovering Maneuver
The main purpose of this article is the structural analysis of a composite blade of a selected helicopter. In this study, the stresses on rotors' blades caused by centrifugal forces, lift, drag and torque are analyzed. The governing equations of the structure behavior and solving processes were carried out by MATLAB software, and simulation is carried out by ABAQUS software, and they are compar...
متن کاملFlight Measurements of the Effects of Simulated Leading-Edge Erosion on Helicopter Blade Stall, Torsional Loads and Performance
The leading edges of the main rotor blades of a Wessex helicopter were artificially roughened to simulate light to moderate erosion of unprotected light alloy blades. Pitch link loads were measured in forward flight for various spanwise extents of leading-edge roughness, and the values of forward speed at which a pre-set limit of oscillatory pitch link load was reached were determined. This lim...
متن کاملStall Flutter Suppression for Absolutely Divergent Motions of Wind Turbine Blade Base on H-Infinity Mixed-Sensitivity Synthesis Method
This paper is devoted to solve the problem of stall flutter suppression for an absolutely divergent blade of small scale wind turbine. The blade is specially designed with absolutely divergent motions for the purpose of determining the most effective methods of active control for stall flutter suppression. A 2-DOF blade section is considered, with a simplified stall nonlinear aerodynamic model ...
متن کاملHelicopter Blade Stability Analysis Using Aeroelastic Frequency Response Functions
In the present paper, the aeroelastic stability of helicopter rotor blade is determined using Aeroelastic Frequency Response Function. The conventional methods of aeroelastic stability usually use an iterative procedure while the present method does not require such approach. Aeroelastic Frequency Response Functions are obtained by inverting dynamic stiffness matrix of the aeroelastic system. S...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: Journal of the Japan Society for Aeronautical and Space Sciences
سال: 1985
ISSN: 0021-4663
DOI: 10.2322/jjsass1969.33.332