Rotor-Blade Coupled Torsional Vibration Evaluation Using Modal Parameters Based on FEM Analysis and Experiment(Mechanical Systems)
نویسندگان
چکیده
منابع مشابه
Modal Vibration Control in Periodic Time-varying Structures with Focus on Rotor-blade Systems
Abstract. In this paper an active controller for a periodic time-variant coupled rotor-blade system is designed. A periodic modal state feedback control scheme is designed based on a modal transformation of the system into a linear time-invariant formulation. The transformation makes it possible to design the controller using classical linear control techniques. Moreover, it provides the possib...
متن کاملA Qualitative Study Of The Effect Of Fatigue Damage Growth On Helicopter Rotor Blade Modal Parameters
Structural damage in materials evolves over time due to growth of fatigue cracks in homogenous materials and a complicated process of matrix cracking, delamination, fiber breakage and fiber matrix debonding in composite materials. In this study, a finite element model of the helicopter rotor blade is used to analyze the effect of damage growth on the modal frequencies. Phenomenological models o...
متن کاملCoupled CFD/CSD Analysis of a Hovering Rotor Using High Fidelity Unsteady Aerodynamics and a Geometrically Exact Rotor Blade Analysis
Abstract: This paper presents a combination of a computational structural dynamics (CSD) and high fidelity unsteady computational fluid dynamics (CFD) analysis. Regarding a helicopter in hover, aerodynamic loads are computed from the three-dimensional Navier-Stokes solver in overlapped grids, and blade motions are obtained from the geometrically exact rotor beam analysis. To couple those analys...
متن کاملCoupled Flap-Lag-Torsional Vibration Analysis of Pre-twisted Non-uniform Helicopter Blades
An approximate numerical mthod is presented for analysis and determination of modal characteristics in straight, pretwisted non-unifom helicopter blades. The analysis considers the coupled flapwise bending (out of plane), chordwise bending (in plane), and torsion vibration of both rotating and non-rotating blades. The proposed method is based on the integral expansion of Green functions (struct...
متن کاملCoupled Flap-Lag-Torsional Vibration Analysis of Pre-twisted Non-uniform Helicopter Blades
An approximate numerical mthod is presented for analysis and determination of modal characteristics in straight, pretwisted non-unifom helicopter blades. The analysis considers the coupled flapwise bending (out of plane), chordwise bending (in plane), and torsion vibration of both rotating and non-rotating blades. The proposed method is based on the integral expansion of Green functions (struct...
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: TRANSACTIONS OF THE JAPAN SOCIETY OF MECHANICAL ENGINEERS Series C
سال: 2010
ISSN: 0387-5024,1884-8354
DOI: 10.1299/kikaic.76.3282