Structural optimization of high speed prop rotors including aeroelastic stability constraints

Aditi Chattopadhyay, T. R. McCarthy, J. F. Madden

Research output: Contribution to journalArticle

4 Citations (Scopus)

Abstract

An optimization procedure is developed to address the problem of aeroelastic stability of high speed prop-rotor aircraft. A composite box beam is used as a perturbational stiffness model and the objective function to be minimized is the perturbational weight. An optimization algorithm, which used the method of feasible directions, is coupled with a hybrid approximate analysis to reduce the computational expense of exact analyses for every function evaluation. The results, compared to a reference rotor which is unstable in both hover and high speed cruise, show significant improvements in the aeroelastic stability without large weight penalties.

Original languageEnglish (US)
Pages (from-to)101-113
Number of pages13
JournalMathematical and Computer Modelling
Volume18
Issue number3-4
DOIs
StatePublished - 1993

Fingerprint

Structural optimization
Structural Optimization
Rotor
High Speed
Rotors
Method of Feasible Directions
Function evaluation
Evaluation Function
Penalty
Aircraft
Stiffness
Optimization Algorithm
Objective function
Unstable
Composite
Optimization
Composite materials
Model
Expenses
Cruise

ASJC Scopus subject areas

  • Computer Science (miscellaneous)
  • Information Systems and Management
  • Control and Systems Engineering
  • Applied Mathematics
  • Computational Mathematics
  • Modeling and Simulation

Cite this

Structural optimization of high speed prop rotors including aeroelastic stability constraints. / Chattopadhyay, Aditi; McCarthy, T. R.; Madden, J. F.

In: Mathematical and Computer Modelling, Vol. 18, No. 3-4, 1993, p. 101-113.

Research output: Contribution to journalArticle

@article{cbef468a34f844c0b639c882ea1b3e5b,
title = "Structural optimization of high speed prop rotors including aeroelastic stability constraints",
abstract = "An optimization procedure is developed to address the problem of aeroelastic stability of high speed prop-rotor aircraft. A composite box beam is used as a perturbational stiffness model and the objective function to be minimized is the perturbational weight. An optimization algorithm, which used the method of feasible directions, is coupled with a hybrid approximate analysis to reduce the computational expense of exact analyses for every function evaluation. The results, compared to a reference rotor which is unstable in both hover and high speed cruise, show significant improvements in the aeroelastic stability without large weight penalties.",
author = "Aditi Chattopadhyay and McCarthy, {T. R.} and Madden, {J. F.}",
year = "1993",
doi = "10.1016/0895-7177(93)90107-A",
language = "English (US)",
volume = "18",
pages = "101--113",
journal = "Mathematical and Computer Modelling",
issn = "0895-7177",
publisher = "Elsevier Limited",
number = "3-4",

}

TY - JOUR

T1 - Structural optimization of high speed prop rotors including aeroelastic stability constraints

AU - Chattopadhyay, Aditi

AU - McCarthy, T. R.

AU - Madden, J. F.

PY - 1993

Y1 - 1993

N2 - An optimization procedure is developed to address the problem of aeroelastic stability of high speed prop-rotor aircraft. A composite box beam is used as a perturbational stiffness model and the objective function to be minimized is the perturbational weight. An optimization algorithm, which used the method of feasible directions, is coupled with a hybrid approximate analysis to reduce the computational expense of exact analyses for every function evaluation. The results, compared to a reference rotor which is unstable in both hover and high speed cruise, show significant improvements in the aeroelastic stability without large weight penalties.

AB - An optimization procedure is developed to address the problem of aeroelastic stability of high speed prop-rotor aircraft. A composite box beam is used as a perturbational stiffness model and the objective function to be minimized is the perturbational weight. An optimization algorithm, which used the method of feasible directions, is coupled with a hybrid approximate analysis to reduce the computational expense of exact analyses for every function evaluation. The results, compared to a reference rotor which is unstable in both hover and high speed cruise, show significant improvements in the aeroelastic stability without large weight penalties.

UR - http://www.scopus.com/inward/record.url?scp=38249001463&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=38249001463&partnerID=8YFLogxK

U2 - 10.1016/0895-7177(93)90107-A

DO - 10.1016/0895-7177(93)90107-A

M3 - Article

VL - 18

SP - 101

EP - 113

JO - Mathematical and Computer Modelling

JF - Mathematical and Computer Modelling

SN - 0895-7177

IS - 3-4

ER -