3 edition of Aeroelasticity and structural optimization of composite helicopter rotor blades with swept tips found in the catalog.
Aeroelasticity and structural optimization of composite helicopter rotor blades with swept tips
by National Aeronautics and Space Administration, Langley Research Center, National Technical Information Service, distributor in Hampton, Va, [Springfield, Va
Written in English
|Statement||K.A. Yuan and P.P. Friedmann.|
|Series||NASA contractor report -- 4665., NASA contractor report -- NASA CR-4665.|
|Contributions||Langley Research Center.|
|The Physical Object|
Aeroelasticity and structural optimization of composite helicopter rotor blades with swept tips [microform]  Yuan, K. A. Hampton, Va.: National Aeronautics and Space Administration, Langley Research Center ; [Springfield, Va.: National Technical Information Service, distributor, ]. Aeroelasticity counteracting blade twist PaulPounds (Aeronautics) (OP) One of the problems of using torsionally soft rotor blades occurs at high collective pitch, if the blade is highly twisted. Swept back blades would go even further down this route (assuming higher rotor rpm is the way to go).
Helicopter rotor blades spin at a relatively high angular speed and, although flexible, are effectively stiffened by centrifugal forces. Because of the free rotation in flap and lead-lag directions at the root in articulated rotors, a large component of their motion is as a rigid body. effects for helicopter rotor blades in hover and forward flight were investigated. To take into account the large deformations of rotor blades, a large deflection beam model was used. Also, to estimate unsteady wakes and calculate its induced velocities, a freewake model w .
materials and the complexity of blade structural layout, obtaining the cross-sectional properties of the composite blades is quite challenging and requires a specialised cross-sectional analysis model. Fig. 1 presents the components of the aeroelastic modelling of wind turbine blades, and each component is reviewed in this paper. 30 S. Murugan et al. / Aerospace Science and Technology 16 () 29–39 Fig. 1. Composite helicopterrotorblade. fects of spatially uncertain material properties on the aeroelastic response predictions of rotor blade and this is the aim of this.
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Aeroelasticity and Structural Optimization of Composite Helicopter Rotor Blades With Swept Tips K. Yuan and P. Friedmann University of California • Los Angeles, California National Aeronautics and Space Administration Langley Research Center • Hampton, Virginia Prepared for Langley Research Center under Grant NAG May File Size: 9MB.
This paper describes the structural optimization of composite helicopter rotor blades with swept tips to minimize the B/rev vibratory hub loads in forward flight subject to frequency and. Get this from a library. Aeroelasticity and structural optimization of composite helicopter rotor blades with swept tips.
[K A Yuan; Langley Research Center.]. Optimization of Composite Rotor Blades For the sixth constraint on the autorotational inertia, the prescribed value of J is ascertained based on the helicopter data available in  for a helicopter of gross weight about pounds and maximum available engine horsepower of about (of which 80% is assumed available for the main rotor).Cited by: AEROELASTIC ANALYSIS OF HELICOPTER ROTOR BLADES INCORPORATING ANISOTROPIC PIEZOELECTRIC TWIST ACTUATION W.
Keats Wilkie W. Keith Belvin NASA Langley Research Center NASA Langley Research Center Aeroelasticity Branch Structural Dynamics Branch Mail Stop Mail Stop Hampton, VirginiaU.S.A. Hampton, Virginiaby: A new aeroelastic model is developed in this study which is suitable for composite rotor blades with swept tips in hover and in forward flight.
The hingeless blade is modeled by beam type finite. wing aerodynamics, dynamics, and aeroelasticity. A more recent book17 treats several aeroelastic and structural dynamic problems in rotorcraft.
Quite recently, Leishman18 has written an excellent book on helicopter aerodynamics, which contains good treatments of unsteady aerodynamics, rotor wake models, and dynamic stall. aeroelasticity. A more recent book  treats several aeroelastic and structural dynamic problems in ro-torcraft.
Quite recently, Leishman  has written an excellent book on helicopter aerodynamics, which contains good treatments of unsteady aerodynamics, rotor wake model, and dynamic stall. Fundamental Differences Between Rotary-Wing and.
Computational-Fluid-Dynamics- and Computational-Structural-Dynamics-Based Time-Accurate Aeroelasticity of Helicopter Rotor Blades G.
Guruswamy∗ NASA Ames Research Center, Moffett Field, California DOI: / A modular capability to compute dynamic aeroelastic characteristics of rotor blades using the Euler/Navier–. A good background on optimization of composite structures was given by Jung 8, Volovoi 9, and Gurdal 10 et al.
Ganguli and Chopra 11 studied aeroelastic optimization of a helicopter rotor blade to reduce vibration and dynamic stresses.
The studies were carried out for a four-bladed hingeless rotor consisting of a two-cell composite box-beam by: 5.
vortex generation. Rotor blades are made out of the variety of materials, including aluminium, composites, and steel or titanium, with abrasion shields along the leading edge. The helicopter rotor hub is powered by the engine, and the rotor blades are attached to the centre.
The motion of blade is controlled by the helicopter rotor system. The mainAuthor: S Mohan Kumar, J Narsaiah, Pininti Sairam Reddy. International Forum on Aeroelasticity and Structural Dynamics IFASD JuneComo - Italy. AEROELASTIC ANALYSIS OF DOUBLE-SWEPT ROTOR BLADE IN HOVERING CONDITIONS. Rohin Kumar1, and Lokeswara Rao.
Institute of Flight Systems, Rotorcraft DLR, Braunschweig, Germany. @ 2 Manager, PhD candidateFile Size: 1MB. APPLICATION OF COMPUTATIONAL AEROELASTICITY TO DESIGN OF HELICOPTER ROTOR BLADES Marcello Righi Zurich University of Applied Sciences, Technikumstrasse 9, Winterthur, Switzerland Keywords: helicopter aeroelasticity aerodynamics structural dynamics Abstract Design of efﬁcient and stable rotors must account for the reciprocal inﬂuence of.
Highly regarded text deals with aeroelasticity as well as underlying aerodynamic and structural tools. Topics include incompressible flow, flutter, model theory, and. Purpose – The purpose of this paper is to present the development and application of a numerical formulation for the structural dynamics and aeroelastic analysis of new generation helicopter and tiltrotor rotor blades.
These are characterized by a curvilinear elastic axis, typically with the presence of tip sweep and anhedral angles. Design/methodology/approach – The structural dynamics.
The final chapters of the book cover aeroservoelasticity wing movement and flight control matters; aerothermoelasticity wing movement and the effects of temperature and thermal stresses; and, aeroelastic design by optimization based on the author s lifetime of work as a consulting aeronautical engineer and teacher in the field of aeroelasticity.
This thesis deals with structural dynamics modeling and simulation in time domain of helicopter blades for computational aeroelasticity. A structural model and an aeroelastic model are provided and a computer program has been developed and tested in this research.
In the structural model, second-order backward Euler method is used to discretize Cited by: In this chapter, four main topics in composite blades of wind turbines including design, stress analysis, aeroelasticity, and fatigue are studied.
For static analysis, finite element method (FEM) is applied and the critical zone is extracted. Moreover, geometry, layup, and loading of the turbine blades made of laminated composites are calculated and by: 1.
Buy Rotary Wing Structural Dynamics and Aeroelasticity, Second Edition (Education Series) (AIAA Education) on FREE SHIPPING on qualified ordersCited by: 5.
The second set had blades of stiffer construction with swept-tips. The purpose of these tests was to measure the isolated rotor aeroelastic stability of bending/torsion coupled rotor blades over a range of flight conditions.
The two soft inplane rotor systems were designed with low first torsion frequency to emphasize the effects of Size: KB. Report presenting an investigation to determine the effects of compressibility on the hovering performance and the blade pitching moments of a helicopter rotor with a tip airfoil, a root airfoil, and twist.
Results regarding hovering performance, rotor-blade pitching moments, rotor profile-drag torque, and a comparison with two-dimensional drag-divergence data are by: 1.
Aeroelastic oscillations of a rotating blade as a thin-walled beam with restrained strains of bending, transverse shear, and torsion are considered. Aerodynamic loads on the blade performing the forced harmonic oscillations at helicopter hovering are determined according to the nonstationary theory of a two-dimensional flow past blade cross-sections without taking into account the vortex wake Author: T.
V. Grishanina, F. N. Shklyarchuk.Yuan, K. A., & Friedmann, P. P. (). Structural optimization for vibratory loads reduction of composite helicopter rotor blades with advanced geometry tips. Journal of the American Helicopter Society, 43, – CrossRef Google Scholar.