5 Citations (Scopus)

Abstract

Some recent efforts at application of structural optimization techniques for minimizing vibration in an articulated rotor blade are described. Two different optimization problems are discussed. In the first, the 4/rev vertical root shear and the blade weight are simultaneously minimized with constraints on natural frequencies, autorotational inertia and centrifugal stress. In the second, a more comprehensive vibration reduction problem is addressed. The 4/rev vertical and the 3/rev inplane shears, at the blade root, are minimized with constraints on the 3/rev radial shear, the 3/rev flapping and torsional moments, the 4/rev lagging moment, natural frequencies, autorotational inertia, centrifugal stress, blade weight and rotor thrust. Rotor aerodynamic and dynamic analyses are coupled with an optimizer to obtain the blade designs for a forward flight condition. The program CAMRAD is used for the blade aerodynamic and dynamic analyses and the program CONMIN is used for optimization. The global criteria approach is used to formulate the multiple objective optimization problem and the optimum designs are compared with a reference blade. A wind tunnel model of an advanced articulated rotor blade is used as the baseline or reference design.

Original languageEnglish (US)
Pages (from-to)37-50
Number of pages14
JournalEngineering Optimization
Volume19
Issue number1
DOIs
StatePublished - Jan 2 1992

Fingerprint

Structural optimization
Structural Optimization
Blade
Rotor
Turbomachine blades
Rotors
Vibration
Natural frequencies
Aerodynamics
Natural Frequency
Inertia
Wind tunnels
Vertical
Roots
Multiple Objective Optimization
Optimization Problem
Moment
Optimization problem
Natural frequency
Wind Tunnel

Keywords

  • dynamics
  • helicopters
  • rotor blades
  • Structural optimization
  • vibrations

ASJC Scopus subject areas

  • Computer Science Applications
  • Industrial and Manufacturing Engineering
  • Management Science and Operations Research
  • Applied Mathematics
  • Control and Optimization

Cite this

Vibration reduction in an articulated rotor blade using structural optimization. / Chattopadhyay, Aditi.

In: Engineering Optimization, Vol. 19, No. 1, 02.01.1992, p. 37-50.

Research output: Contribution to journalArticle

@article{b50faaf915114e75b8c288cd5a65075f,
title = "Vibration reduction in an articulated rotor blade using structural optimization",
abstract = "Some recent efforts at application of structural optimization techniques for minimizing vibration in an articulated rotor blade are described. Two different optimization problems are discussed. In the first, the 4/rev vertical root shear and the blade weight are simultaneously minimized with constraints on natural frequencies, autorotational inertia and centrifugal stress. In the second, a more comprehensive vibration reduction problem is addressed. The 4/rev vertical and the 3/rev inplane shears, at the blade root, are minimized with constraints on the 3/rev radial shear, the 3/rev flapping and torsional moments, the 4/rev lagging moment, natural frequencies, autorotational inertia, centrifugal stress, blade weight and rotor thrust. Rotor aerodynamic and dynamic analyses are coupled with an optimizer to obtain the blade designs for a forward flight condition. The program CAMRAD is used for the blade aerodynamic and dynamic analyses and the program CONMIN is used for optimization. The global criteria approach is used to formulate the multiple objective optimization problem and the optimum designs are compared with a reference blade. A wind tunnel model of an advanced articulated rotor blade is used as the baseline or reference design.",
keywords = "dynamics, helicopters, rotor blades, Structural optimization, vibrations",
author = "Aditi Chattopadhyay",
year = "1992",
month = "1",
day = "2",
doi = "10.1080/03052159208941219",
language = "English (US)",
volume = "19",
pages = "37--50",
journal = "Engineering Optimization",
issn = "0305-215X",
publisher = "Taylor and Francis Ltd.",
number = "1",

}

TY - JOUR

T1 - Vibration reduction in an articulated rotor blade using structural optimization

AU - Chattopadhyay, Aditi

PY - 1992/1/2

Y1 - 1992/1/2

N2 - Some recent efforts at application of structural optimization techniques for minimizing vibration in an articulated rotor blade are described. Two different optimization problems are discussed. In the first, the 4/rev vertical root shear and the blade weight are simultaneously minimized with constraints on natural frequencies, autorotational inertia and centrifugal stress. In the second, a more comprehensive vibration reduction problem is addressed. The 4/rev vertical and the 3/rev inplane shears, at the blade root, are minimized with constraints on the 3/rev radial shear, the 3/rev flapping and torsional moments, the 4/rev lagging moment, natural frequencies, autorotational inertia, centrifugal stress, blade weight and rotor thrust. Rotor aerodynamic and dynamic analyses are coupled with an optimizer to obtain the blade designs for a forward flight condition. The program CAMRAD is used for the blade aerodynamic and dynamic analyses and the program CONMIN is used for optimization. The global criteria approach is used to formulate the multiple objective optimization problem and the optimum designs are compared with a reference blade. A wind tunnel model of an advanced articulated rotor blade is used as the baseline or reference design.

AB - Some recent efforts at application of structural optimization techniques for minimizing vibration in an articulated rotor blade are described. Two different optimization problems are discussed. In the first, the 4/rev vertical root shear and the blade weight are simultaneously minimized with constraints on natural frequencies, autorotational inertia and centrifugal stress. In the second, a more comprehensive vibration reduction problem is addressed. The 4/rev vertical and the 3/rev inplane shears, at the blade root, are minimized with constraints on the 3/rev radial shear, the 3/rev flapping and torsional moments, the 4/rev lagging moment, natural frequencies, autorotational inertia, centrifugal stress, blade weight and rotor thrust. Rotor aerodynamic and dynamic analyses are coupled with an optimizer to obtain the blade designs for a forward flight condition. The program CAMRAD is used for the blade aerodynamic and dynamic analyses and the program CONMIN is used for optimization. The global criteria approach is used to formulate the multiple objective optimization problem and the optimum designs are compared with a reference blade. A wind tunnel model of an advanced articulated rotor blade is used as the baseline or reference design.

KW - dynamics

KW - helicopters

KW - rotor blades

KW - Structural optimization

KW - vibrations

UR - http://www.scopus.com/inward/record.url?scp=28144454153&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=28144454153&partnerID=8YFLogxK

U2 - 10.1080/03052159208941219

DO - 10.1080/03052159208941219

M3 - Article

VL - 19

SP - 37

EP - 50

JO - Engineering Optimization

JF - Engineering Optimization

SN - 0305-215X

IS - 1

ER -