TY - JOUR
T1 - Multilevel decomposition procedure for efficient design optimization of helicopter rotor blades
AU - Chattopadhyay, Aditi
AU - McCarthy, Thomas R.
AU - Pagaldipti, Narayanan
PY - 1995/2
Y1 - 1995/2
N2 - This paper addresses a multilevel decomposition procedure, for efficient design optimization of helicopter blades, with the coupling of aerodynamics, blade dynamics, aeroelasticity, and structures. The multidisciplinary optimization problem is decomposed into three levels. The rotor is optimized for improved aerodynamic performance at the first level. At the second level, the objective is to improve the dynamic and aeroelastic characteristics of the rotor. A structural optimization is performed at the third level. Interdisciplinary coupling is established through the use of optimal sensitivity derivatives. The Kreisselmeier-Steinhauser function approach is used to formulate the optimization problem when multiple design objectives are involved. A nonlinear programming technique and an approximate analysis procedure are used for optimization. Results obtained show significant improvements in the rotor aerodynamic, dynamic, and structural characteristics, when compared with a reference or baseline rotor.
AB - This paper addresses a multilevel decomposition procedure, for efficient design optimization of helicopter blades, with the coupling of aerodynamics, blade dynamics, aeroelasticity, and structures. The multidisciplinary optimization problem is decomposed into three levels. The rotor is optimized for improved aerodynamic performance at the first level. At the second level, the objective is to improve the dynamic and aeroelastic characteristics of the rotor. A structural optimization is performed at the third level. Interdisciplinary coupling is established through the use of optimal sensitivity derivatives. The Kreisselmeier-Steinhauser function approach is used to formulate the optimization problem when multiple design objectives are involved. A nonlinear programming technique and an approximate analysis procedure are used for optimization. Results obtained show significant improvements in the rotor aerodynamic, dynamic, and structural characteristics, when compared with a reference or baseline rotor.
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U2 - 10.2514/3.12424
DO - 10.2514/3.12424
M3 - Article
AN - SCOPUS:0029240060
SN - 0001-1452
VL - 33
SP - 223
EP - 230
JO - AIAA journal
JF - AIAA journal
IS - 2
ER -