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Title: Aeroelastic behavior of composite helicopter rotor blades with advanced geometry tips

Abstract

A new structural and aeroelastic model capable of representing the aeroelastic stability and response of composite helicopter rotor blades with advanced geometry tips is presented. Where it is understood that advanced geometry tips are blade tips having sweep, anhedral and taper in the outboard 10% segment of the blade. The blade is modeled by beam finite elements. A single element is used to represent the swept tip. The nonlinear equations of motion are derived using the Hamilton`s principle and are based on moderate deflection theory. Thus, the nonlinearities are of the geometric type. The important structural blade attributes captured by the model are arbitrary cross-sectional shape, general anisotropic material behavior, transverse shear and out-of-plane warping. The aerodynamic loads are based on quasi-steady Greenberg theory with reverse flow effects, using an implicit formulation. The nonlinear aeroelastic response of the blade is obtained from a fully coupled propulsive trim/aeroelastic response analysis. Aeroelastic stability is obtained from linearizing the equations of motion about the steady state response of the blade and using Floquet theory. Numerical results for the aeroelastic stability and response of a hingeless composite blade with two cell type cross section are presented, together with vibratory hub shears and moments. Themore » influence of ply orientation and tip sweep is clearly illustrated by the results.« less

Authors:
;  [1]
  1. Univ. of California, Los Angeles, CA (United States)
Publication Date:
OSTI Identifier:
175181
Report Number(s):
CONF-950686-
TRN: 95:006111-0101
Resource Type:
Conference
Resource Relation:
Conference: Joint applied mechanics and materials summer meeting, Los Angeles, CA (United States), 28-30 Jun 1995; Other Information: PBD: 1995; Related Information: Is Part Of AMD - MD `95: Summer conference; PB: 520 p.
Country of Publication:
United States
Language:
English
Subject:
36 MATERIALS SCIENCE; 99 MATHEMATICS, COMPUTERS, INFORMATION SCIENCE, MANAGEMENT, LAW, MISCELLANEOUS; 33 ADVANCED PROPULSION SYSTEMS; COMPOSITE MATERIALS; STABILITY; EQUATIONS OF MOTION; SHEAR; AIRCRAFT COMPONENTS; HELICOPTERS; AERODYNAMICS; ELASTICITY; MATHEMATICAL MODELS

Citation Formats

Friedmann, P P, and Yuan, K A. Aeroelastic behavior of composite helicopter rotor blades with advanced geometry tips. United States: N. p., 1995. Web.
Friedmann, P P, & Yuan, K A. Aeroelastic behavior of composite helicopter rotor blades with advanced geometry tips. United States.
Friedmann, P P, and Yuan, K A. Sun . "Aeroelastic behavior of composite helicopter rotor blades with advanced geometry tips". United States.
@article{osti_175181,
title = {Aeroelastic behavior of composite helicopter rotor blades with advanced geometry tips},
author = {Friedmann, P P and Yuan, K A},
abstractNote = {A new structural and aeroelastic model capable of representing the aeroelastic stability and response of composite helicopter rotor blades with advanced geometry tips is presented. Where it is understood that advanced geometry tips are blade tips having sweep, anhedral and taper in the outboard 10% segment of the blade. The blade is modeled by beam finite elements. A single element is used to represent the swept tip. The nonlinear equations of motion are derived using the Hamilton`s principle and are based on moderate deflection theory. Thus, the nonlinearities are of the geometric type. The important structural blade attributes captured by the model are arbitrary cross-sectional shape, general anisotropic material behavior, transverse shear and out-of-plane warping. The aerodynamic loads are based on quasi-steady Greenberg theory with reverse flow effects, using an implicit formulation. The nonlinear aeroelastic response of the blade is obtained from a fully coupled propulsive trim/aeroelastic response analysis. Aeroelastic stability is obtained from linearizing the equations of motion about the steady state response of the blade and using Floquet theory. Numerical results for the aeroelastic stability and response of a hingeless composite blade with two cell type cross section are presented, together with vibratory hub shears and moments. The influence of ply orientation and tip sweep is clearly illustrated by the results.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {1995},
month = {12}
}

Conference:
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